NACA 22112 (naca22112-jf) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 22112 (naca22112-jf) Reynolds number: 1,000,000 Max Cl/Cd: 89.4 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca22112-jf-1000000-n5.txt Download as CSV file: xf-naca22112-jf-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 22112
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -1.2208 0.07437 0.07158 -0.0206 1.0000 0.0095
-17.250 -1.2493 0.06574 0.06276 -0.0259 1.0000 0.0095
-17.000 -1.2687 0.05901 0.05586 -0.0299 1.0000 0.0095
-16.750 -1.2819 0.05361 0.05031 -0.0327 1.0000 0.0095
-16.500 -1.2903 0.04919 0.04575 -0.0347 1.0000 0.0096
-16.250 -1.2956 0.04545 0.04188 -0.0360 1.0000 0.0096
-16.000 -1.2990 0.04217 0.03848 -0.0368 1.0000 0.0097
-15.750 -1.2998 0.03943 0.03562 -0.0370 1.0000 0.0098
-15.500 -1.2987 0.03705 0.03313 -0.0368 1.0000 0.0098
-15.250 -1.2963 0.03496 0.03093 -0.0361 1.0000 0.0099
-15.000 -1.2926 0.03312 0.02898 -0.0351 1.0000 0.0100
-14.750 -1.2875 0.03149 0.02725 -0.0339 1.0000 0.0101
-14.500 -1.2813 0.03005 0.02570 -0.0323 1.0000 0.0102
-14.250 -1.2739 0.02876 0.02431 -0.0306 1.0000 0.0103
-14.000 -1.2649 0.02763 0.02308 -0.0288 1.0000 0.0104
-13.750 -1.2550 0.02660 0.02196 -0.0269 1.0000 0.0105
-13.500 -1.2445 0.02564 0.02092 -0.0248 1.0000 0.0106
-13.250 -1.2326 0.02477 0.01996 -0.0227 1.0000 0.0108
-13.000 -1.2183 0.02392 0.01902 -0.0210 1.0000 0.0109
-12.750 -1.2023 0.02309 0.01810 -0.0195 1.0000 0.0110
-12.500 -1.1851 0.02230 0.01722 -0.0181 1.0000 0.0111
-12.250 -1.1670 0.02156 0.01639 -0.0168 1.0000 0.0112
-12.000 -1.1492 0.02075 0.01551 -0.0155 1.0000 0.0113
-11.750 -1.1313 0.01992 0.01461 -0.0141 1.0000 0.0115
-11.500 -1.1115 0.01926 0.01390 -0.0130 1.0000 0.0117
-11.250 -1.0907 0.01869 0.01329 -0.0119 1.0000 0.0119
-11.000 -1.0692 0.01816 0.01273 -0.0109 1.0000 0.0120
-10.750 -1.0475 0.01767 0.01220 -0.0100 1.0000 0.0122
-10.500 -1.0256 0.01718 0.01167 -0.0090 1.0000 0.0124
-10.250 -1.0037 0.01671 0.01116 -0.0080 1.0000 0.0126
-10.000 -0.9818 0.01625 0.01065 -0.0069 1.0000 0.0129
-9.750 -0.9601 0.01579 0.01016 -0.0058 1.0000 0.0131
-9.500 -0.9386 0.01535 0.00968 -0.0046 1.0000 0.0133
-9.250 -0.9174 0.01494 0.00922 -0.0034 1.0000 0.0135
-9.000 -0.8963 0.01455 0.00880 -0.0020 1.0000 0.0137
-8.750 -0.8752 0.01420 0.00841 -0.0007 1.0000 0.0139
-8.500 -0.8529 0.01372 0.00791 0.0003 0.9995 0.0144
-8.250 -0.8216 0.01333 0.00752 -0.0005 0.9972 0.0148
-8.000 -0.7896 0.01297 0.00715 -0.0015 0.9950 0.0151
-7.750 -0.7580 0.01261 0.00678 -0.0024 0.9924 0.0155
-7.500 -0.7274 0.01227 0.00641 -0.0030 0.9883 0.0160
-7.250 -0.6957 0.01193 0.00605 -0.0039 0.9842 0.0164
-7.000 -0.6658 0.01162 0.00572 -0.0043 0.9783 0.0168
-6.750 -0.6353 0.01128 0.00535 -0.0048 0.9719 0.0172
-6.500 -0.6067 0.01096 0.00503 -0.0049 0.9632 0.0178
-6.250 -0.5779 0.01070 0.00478 -0.0050 0.9532 0.0184
-6.000 -0.5506 0.01049 0.00454 -0.0048 0.9404 0.0190
-5.750 -0.5243 0.01029 0.00430 -0.0042 0.9251 0.0197
-5.500 -0.4984 0.01011 0.00406 -0.0036 0.9082 0.0203
-5.250 -0.4728 0.00989 0.00379 -0.0030 0.8893 0.0210
-5.000 -0.4468 0.00973 0.00357 -0.0024 0.8688 0.0218
-4.750 -0.4206 0.00960 0.00338 -0.0019 0.8467 0.0227
-4.500 -0.3942 0.00950 0.00318 -0.0014 0.8240 0.0236
-4.250 -0.3675 0.00940 0.00301 -0.0009 0.8002 0.0245
-4.000 -0.3410 0.00929 0.00282 -0.0005 0.7752 0.0260
-3.750 -0.3140 0.00921 0.00267 -0.0002 0.7506 0.0273
-3.500 -0.2870 0.00915 0.00252 0.0002 0.7254 0.0285
-3.250 -0.2599 0.00908 0.00238 0.0005 0.7000 0.0301
-3.000 -0.2328 0.00903 0.00226 0.0007 0.6740 0.0323
-2.750 -0.2055 0.00902 0.00215 0.0010 0.6445 0.0342
-2.500 -0.1787 0.00902 0.00203 0.0013 0.6054 0.0372
-2.250 -0.1517 0.00906 0.00194 0.0016 0.5628 0.0401
-2.000 -0.1245 0.00906 0.00185 0.0018 0.5312 0.0449
-1.750 -0.0970 0.00905 0.00177 0.0019 0.5068 0.0512
-1.500 -0.0696 0.00901 0.00170 0.0021 0.4823 0.0619
-1.250 -0.0467 0.00828 0.00146 0.0028 0.4588 0.2346
-1.000 -0.0218 0.00788 0.00135 0.0032 0.4389 0.3376
-0.750 0.0041 0.00763 0.00129 0.0035 0.4194 0.4109
-0.500 0.0300 0.00742 0.00126 0.0039 0.3990 0.4820
-0.250 0.0562 0.00731 0.00124 0.0042 0.3746 0.5386
0.000 0.0827 0.00723 0.00125 0.0045 0.3516 0.5868
0.250 0.1091 0.00716 0.00126 0.0048 0.3309 0.6367
0.500 0.1354 0.00711 0.00129 0.0052 0.3112 0.6839
0.750 0.1613 0.00706 0.00134 0.0057 0.2923 0.7332
1.000 0.1884 0.00712 0.00139 0.0059 0.2719 0.7583
1.250 0.2155 0.00721 0.00145 0.0062 0.2502 0.7786
1.500 0.2425 0.00730 0.00152 0.0064 0.2315 0.7985
1.750 0.2697 0.00739 0.00160 0.0067 0.2159 0.8179
2.000 0.2969 0.00748 0.00168 0.0069 0.2021 0.8361
2.250 0.3240 0.00758 0.00177 0.0072 0.1896 0.8534
2.500 0.3510 0.00769 0.00187 0.0074 0.1776 0.8697
2.750 0.3780 0.00781 0.00198 0.0077 0.1674 0.8848
3.000 0.4053 0.00790 0.00209 0.0080 0.1612 0.8986
3.250 0.4325 0.00803 0.00220 0.0082 0.1546 0.9114
3.500 0.4597 0.00814 0.00232 0.0085 0.1495 0.9236
3.750 0.4872 0.00827 0.00244 0.0087 0.1445 0.9340
4.000 0.5147 0.00842 0.00257 0.0088 0.1396 0.9434
4.250 0.5428 0.00855 0.00270 0.0088 0.1363 0.9521
4.500 0.5715 0.00868 0.00283 0.0087 0.1336 0.9591
4.750 0.6009 0.00884 0.00298 0.0084 0.1300 0.9656
5.000 0.6297 0.00901 0.00313 0.0082 0.1260 0.9715
5.250 0.6612 0.00919 0.00330 0.0074 0.1230 0.9754
5.500 0.6914 0.00933 0.00345 0.0069 0.1211 0.9800
5.750 0.7216 0.00949 0.00361 0.0063 0.1181 0.9839
6.000 0.7541 0.00968 0.00378 0.0052 0.1148 0.9861
6.250 0.7864 0.00990 0.00397 0.0041 0.1114 0.9883
6.500 0.8183 0.01007 0.00416 0.0031 0.1091 0.9906
6.750 0.8495 0.01025 0.00435 0.0023 0.1068 0.9930
7.000 0.8813 0.01045 0.00455 0.0013 0.1039 0.9946
7.250 0.9136 0.01068 0.00476 0.0002 0.1003 0.9960
7.500 0.9454 0.01091 0.00499 -0.0009 0.0975 0.9975
7.750 0.9770 0.01111 0.00520 -0.0019 0.0952 0.9990
8.000 1.0066 0.01133 0.00543 -0.0024 0.0921 1.0000
8.250 1.0286 0.01157 0.00566 -0.0014 0.0890 1.0000
8.500 1.0509 0.01181 0.00590 -0.0004 0.0863 1.0000
8.750 1.0736 0.01201 0.00613 0.0005 0.0840 1.0000
9.000 1.0961 0.01226 0.00638 0.0014 0.0809 1.0000
9.250 1.1183 0.01255 0.00665 0.0023 0.0775 1.0000
9.500 1.1409 0.01282 0.00693 0.0031 0.0749 1.0000
9.750 1.1637 0.01309 0.00723 0.0039 0.0719 1.0000
10.000 1.1860 0.01344 0.00755 0.0048 0.0682 1.0000
10.250 1.2088 0.01375 0.00788 0.0055 0.0653 1.0000
10.500 1.2317 0.01408 0.00824 0.0061 0.0621 1.0000
10.750 1.2536 0.01451 0.00864 0.0069 0.0582 1.0000
11.000 1.2764 0.01487 0.00902 0.0075 0.0553 1.0000
11.250 1.2982 0.01532 0.00947 0.0083 0.0517 1.0000
11.500 1.3200 0.01575 0.00992 0.0090 0.0488 1.0000
11.750 1.3414 0.01622 0.01040 0.0097 0.0456 1.0000
12.000 1.3618 0.01676 0.01094 0.0106 0.0424 1.0000
12.250 1.3825 0.01725 0.01146 0.0114 0.0397 1.0000
12.500 1.4015 0.01787 0.01209 0.0124 0.0368 1.0000
12.750 1.4210 0.01841 0.01266 0.0133 0.0345 1.0000
13.000 1.4385 0.01909 0.01336 0.0144 0.0318 1.0000
13.250 1.4562 0.01970 0.01401 0.0155 0.0299 1.0000
13.500 1.4722 0.02039 0.01474 0.0168 0.0279 1.0000
13.750 1.4849 0.02113 0.01551 0.0186 0.0262 1.0000
14.000 1.4971 0.02186 0.01629 0.0204 0.0247 1.0000
14.250 1.5074 0.02275 0.01723 0.0222 0.0232 1.0000
14.500 1.5173 0.02371 0.01824 0.0239 0.0219 1.0000
14.750 1.5272 0.02472 0.01931 0.0254 0.0209 1.0000
15.000 1.5352 0.02593 0.02058 0.0267 0.0199 1.0000
15.250 1.5413 0.02735 0.02207 0.0279 0.0189 1.0000
15.500 1.5480 0.02883 0.02363 0.0288 0.0182 1.0000
15.750 1.5535 0.03052 0.02541 0.0294 0.0175 1.0000
16.000 1.5569 0.03255 0.02752 0.0298 0.0169 1.0000
16.250 1.5576 0.03499 0.03005 0.0297 0.0162 1.0000
16.500 1.5559 0.03790 0.03304 0.0292 0.0156 1.0000
16.750 1.5541 0.04099 0.03625 0.0284 0.0152 1.0000
17.000 1.5497 0.04459 0.03996 0.0271 0.0148 1.0000
17.250 1.5414 0.04888 0.04438 0.0253 0.0144 1.0000
17.500 1.5285 0.05397 0.04960 0.0230 0.0142 1.0000
17.750 1.5102 0.05999 0.05577 0.0201 0.0140 1.0000
18.000 1.4855 0.06712 0.06305 0.0166 0.0139 1.0000
18.250 1.4536 0.07554 0.07165 0.0125 0.0139 1.0000
18.500 1.4138 0.08547 0.08177 0.0077 0.0141 1.0000
18.750 1.3660 0.09692 0.09342 0.0021 0.0144 1.0000
19.000 1.3135 0.10951 0.10621 -0.0041 0.0147 1.0000
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