NACA 22112 (naca22112-jf) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 22112 (naca22112-jf) Reynolds number: 500,000 Max Cl/Cd: 71.58 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca22112-jf-500000-n5.txt Download as CSV file: xf-naca22112-jf-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.9018 0.05655 0.05345 -0.0332 1.0000 0.0125
-12.250 -1.0298 0.03856 0.03435 -0.0301 1.0000 0.0130
-12.000 -1.0479 0.03435 0.02969 -0.0259 1.0000 0.0133
-11.750 -1.0481 0.03137 0.02635 -0.0233 1.0000 0.0136
-11.500 -1.0401 0.02923 0.02392 -0.0212 1.0000 0.0138
-11.250 -1.0281 0.02755 0.02202 -0.0194 1.0000 0.0140
-11.000 -1.0128 0.02638 0.02074 -0.0179 1.0000 0.0142
-10.750 -0.9952 0.02549 0.01978 -0.0167 1.0000 0.0143
-10.500 -0.9764 0.02472 0.01895 -0.0155 1.0000 0.0145
-10.250 -0.9571 0.02396 0.01812 -0.0143 1.0000 0.0147
-10.000 -0.9374 0.02319 0.01727 -0.0132 1.0000 0.0150
-9.750 -0.9175 0.02239 0.01638 -0.0120 1.0000 0.0153
-9.500 -0.8973 0.02161 0.01551 -0.0108 1.0000 0.0157
-9.250 -0.8771 0.02080 0.01459 -0.0096 1.0000 0.0161
-9.000 -0.8569 0.01999 0.01366 -0.0083 1.0000 0.0165
-8.750 -0.8368 0.01924 0.01278 -0.0070 1.0000 0.0168
-8.500 -0.8175 0.01845 0.01194 -0.0055 1.0000 0.0172
-8.250 -0.7978 0.01786 0.01134 -0.0040 1.0000 0.0175
-8.000 -0.7777 0.01737 0.01083 -0.0026 1.0000 0.0178
-7.750 -0.7576 0.01691 0.01035 -0.0012 1.0000 0.0181
-7.500 -0.7378 0.01645 0.00985 0.0004 1.0000 0.0186
-7.250 -0.7184 0.01597 0.00934 0.0020 1.0000 0.0190
-7.000 -0.6877 0.01541 0.00872 0.0012 0.9973 0.0196
-6.750 -0.6545 0.01490 0.00814 0.0000 0.9943 0.0203
-6.500 -0.6231 0.01434 0.00759 -0.0009 0.9902 0.0210
-6.250 -0.5899 0.01394 0.00719 -0.0022 0.9860 0.0217
-6.000 -0.5571 0.01352 0.00676 -0.0033 0.9815 0.0225
-5.750 -0.5264 0.01310 0.00631 -0.0039 0.9745 0.0233
-5.500 -0.4946 0.01270 0.00588 -0.0047 0.9679 0.0242
-5.250 -0.4645 0.01227 0.00545 -0.0052 0.9589 0.0251
-5.000 -0.4345 0.01198 0.00516 -0.0056 0.9485 0.0263
-4.750 -0.4049 0.01169 0.00485 -0.0058 0.9365 0.0276
-4.500 -0.3769 0.01141 0.00453 -0.0056 0.9220 0.0287
-4.250 -0.3505 0.01110 0.00420 -0.0051 0.9050 0.0300
-4.000 -0.3243 0.01088 0.00394 -0.0046 0.8860 0.0315
-3.750 -0.2982 0.01071 0.00371 -0.0039 0.8650 0.0333
-3.500 -0.2724 0.01053 0.00345 -0.0032 0.8427 0.0353
-3.250 -0.2465 0.01038 0.00323 -0.0026 0.8193 0.0375
-3.000 -0.2204 0.01027 0.00303 -0.0020 0.7944 0.0400
-2.750 -0.1942 0.01015 0.00284 -0.0015 0.7693 0.0434
-2.500 -0.1679 0.01008 0.00267 -0.0010 0.7430 0.0475
-2.250 -0.1415 0.00999 0.00250 -0.0005 0.7161 0.0534
-2.000 -0.1154 0.00993 0.00235 0.0000 0.6845 0.0638
-1.750 -0.0945 0.00914 0.00202 0.0011 0.6468 0.2343
-1.500 -0.0728 0.00859 0.00184 0.0020 0.6068 0.3732
-1.250 -0.0490 0.00827 0.00174 0.0028 0.5753 0.4645
-1.000 -0.0242 0.00804 0.00169 0.0034 0.5524 0.5342
-0.750 0.0006 0.00786 0.00166 0.0041 0.5276 0.5979
-0.500 0.0257 0.00776 0.00165 0.0047 0.5015 0.6516
-0.250 0.0510 0.00770 0.00166 0.0054 0.4769 0.6978
0.000 0.0761 0.00764 0.00169 0.0062 0.4549 0.7473
0.250 0.1015 0.00762 0.00175 0.0070 0.4326 0.7907
0.500 0.1276 0.00769 0.00180 0.0075 0.4077 0.8170
0.750 0.1543 0.00780 0.00185 0.0079 0.3819 0.8358
1.250 0.2079 0.00806 0.00199 0.0087 0.3356 0.8700
1.500 0.2349 0.00821 0.00208 0.0091 0.3135 0.8852
1.750 0.2620 0.00839 0.00218 0.0094 0.2908 0.8989
2.000 0.2892 0.00858 0.00228 0.0096 0.2674 0.9117
2.250 0.3166 0.00879 0.00240 0.0098 0.2463 0.9236
2.500 0.3454 0.00900 0.00253 0.0097 0.2286 0.9331
3.000 0.4040 0.00941 0.00280 0.0092 0.1985 0.9501
3.250 0.4333 0.00962 0.00294 0.0089 0.1861 0.9577
3.500 0.4653 0.00983 0.00310 0.0080 0.1763 0.9632
3.750 0.4940 0.01004 0.00325 0.0078 0.1683 0.9703
4.000 0.5279 0.01023 0.00342 0.0065 0.1618 0.9737
4.250 0.5605 0.01045 0.00360 0.0054 0.1551 0.9777
4.500 0.5916 0.01066 0.00379 0.0046 0.1499 0.9823
4.750 0.6259 0.01085 0.00397 0.0032 0.1455 0.9848
5.000 0.6600 0.01108 0.00417 0.0017 0.1411 0.9872
5.250 0.6931 0.01133 0.00440 0.0004 0.1368 0.9902
5.500 0.7254 0.01151 0.00460 -0.0006 0.1336 0.9932
5.750 0.7589 0.01173 0.00482 -0.0020 0.1302 0.9953
6.000 0.7921 0.01198 0.00505 -0.0033 0.1265 0.9975
6.250 0.8248 0.01226 0.00532 -0.0046 0.1229 0.9996
6.500 0.8494 0.01243 0.00553 -0.0041 0.1208 1.0000
6.750 0.8717 0.01263 0.00576 -0.0030 0.1182 1.0000
7.000 0.8938 0.01286 0.00599 -0.0020 0.1153 1.0000
7.250 0.9157 0.01312 0.00624 -0.0010 0.1124 1.0000
7.500 0.9374 0.01340 0.00654 0.0001 0.1099 1.0000
7.750 0.9601 0.01361 0.00679 0.0010 0.1077 1.0000
8.000 0.9826 0.01385 0.00706 0.0019 0.1050 1.0000
8.250 1.0049 0.01411 0.00734 0.0029 0.1022 1.0000
8.500 1.0267 0.01443 0.00765 0.0039 0.0992 1.0000
8.750 1.0490 0.01472 0.00798 0.0048 0.0969 1.0000
9.000 1.0718 0.01499 0.00830 0.0056 0.0942 1.0000
9.250 1.0944 0.01529 0.00863 0.0064 0.0912 1.0000
9.500 1.1165 0.01565 0.00898 0.0072 0.0880 1.0000
9.750 1.1390 0.01600 0.00937 0.0079 0.0854 1.0000
10.000 1.1618 0.01632 0.00975 0.0086 0.0824 1.0000
10.250 1.1840 0.01670 0.01014 0.0093 0.0791 1.0000
10.500 1.2056 0.01714 0.01059 0.0101 0.0758 1.0000
10.750 1.2278 0.01752 0.01103 0.0108 0.0729 1.0000
11.000 1.2492 0.01796 0.01150 0.0116 0.0695 1.0000
11.250 1.2696 0.01847 0.01203 0.0124 0.0663 1.0000
11.500 1.2906 0.01892 0.01255 0.0132 0.0633 1.0000
11.750 1.3103 0.01947 0.01312 0.0141 0.0598 1.0000
12.000 1.3291 0.02006 0.01374 0.0151 0.0568 1.0000
12.250 1.3478 0.02063 0.01437 0.0161 0.0536 1.0000
12.500 1.3643 0.02134 0.01510 0.0173 0.0504 1.0000
12.750 1.3809 0.02199 0.01582 0.0185 0.0478 1.0000
13.000 1.3941 0.02273 0.01660 0.0202 0.0450 1.0000
13.250 1.4052 0.02358 0.01749 0.0221 0.0426 1.0000
13.500 1.4168 0.02442 0.01841 0.0237 0.0403 1.0000
13.750 1.4263 0.02547 0.01951 0.0253 0.0380 1.0000
14.000 1.4348 0.02662 0.02074 0.0268 0.0362 1.0000
14.250 1.4433 0.02785 0.02205 0.0280 0.0343 1.0000
14.500 1.4490 0.02938 0.02365 0.0291 0.0325 1.0000
14.750 1.4532 0.03114 0.02550 0.0299 0.0310 1.0000
15.000 1.4580 0.03300 0.02745 0.0304 0.0296 1.0000
15.250 1.4600 0.03525 0.02981 0.0305 0.0283 1.0000
15.500 1.4590 0.03803 0.03269 0.0302 0.0272 1.0000
15.750 1.4560 0.04124 0.03601 0.0293 0.0263 1.0000
16.000 1.4530 0.04467 0.03958 0.0281 0.0255 1.0000
16.250 1.4462 0.04877 0.04382 0.0264 0.0247 1.0000
16.500 1.4351 0.05364 0.04883 0.0242 0.0241 1.0000
16.750 1.4193 0.05938 0.05472 0.0214 0.0237 1.0000
17.000 1.3982 0.06605 0.06154 0.0181 0.0234 1.0000
17.250 1.3721 0.07366 0.06932 0.0143 0.0232 1.0000
17.500 1.3414 0.08216 0.07799 0.0101 0.0232 1.0000
17.750 1.3075 0.09139 0.08739 0.0056 0.0233 1.0000
18.000 1.2727 0.10096 0.09712 0.0009 0.0234 1.0000
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