NPL 9626 AIRFOIL (npl9626-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9626 AIRFOIL (npl9626-il) Reynolds number: 500,000 Max Cl/Cd: 60.37 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9626-il-500000-n5.txt Download as CSV file: xf-npl9626-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9626 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9458 0.12120 0.11821 0.0058 1.0000 0.0098
-16.500 -1.0005 0.10500 0.10180 -0.0030 1.0000 0.0097
-16.250 -1.0383 0.09315 0.08977 -0.0097 1.0000 0.0096
-16.000 -1.0699 0.08304 0.07949 -0.0155 1.0000 0.0095
-15.750 -1.0957 0.07436 0.07062 -0.0207 1.0000 0.0095
-15.500 -1.1166 0.06670 0.06279 -0.0253 1.0000 0.0095
-15.250 -1.1331 0.06005 0.05596 -0.0294 1.0000 0.0095
-15.000 -1.1455 0.05433 0.05007 -0.0328 1.0000 0.0095
-14.750 -1.1549 0.04944 0.04501 -0.0355 1.0000 0.0095
-14.500 -1.1613 0.04530 0.04070 -0.0374 1.0000 0.0096
-14.250 -1.1655 0.04179 0.03704 -0.0385 1.0000 0.0096
-14.000 -1.1675 0.03882 0.03392 -0.0389 1.0000 0.0097
-13.750 -1.1678 0.03629 0.03124 -0.0387 1.0000 0.0097
-13.500 -1.1665 0.03413 0.02893 -0.0380 1.0000 0.0098
-13.250 -1.1634 0.03229 0.02694 -0.0369 1.0000 0.0099
-13.000 -1.1588 0.03068 0.02521 -0.0353 1.0000 0.0099
-12.750 -1.1527 0.02929 0.02369 -0.0336 1.0000 0.0100
-12.500 -1.1454 0.02806 0.02233 -0.0316 1.0000 0.0101
-12.250 -1.1369 0.02697 0.02113 -0.0294 1.0000 0.0102
-12.000 -1.1258 0.02597 0.02002 -0.0275 1.0000 0.0102
-11.750 -1.1133 0.02490 0.01885 -0.0258 1.0000 0.0104
-11.500 -1.1002 0.02381 0.01768 -0.0241 1.0000 0.0105
-11.250 -1.0851 0.02285 0.01665 -0.0226 1.0000 0.0107
-11.000 -1.0683 0.02201 0.01574 -0.0213 1.0000 0.0109
-10.750 -1.0503 0.02124 0.01490 -0.0200 1.0000 0.0111
-10.500 -1.0318 0.02051 0.01410 -0.0188 1.0000 0.0114
-10.250 -1.0128 0.01981 0.01334 -0.0176 1.0000 0.0117
-10.000 -0.9934 0.01915 0.01260 -0.0164 1.0000 0.0120
-9.750 -0.9739 0.01852 0.01189 -0.0152 1.0000 0.0124
-9.500 -0.9544 0.01790 0.01122 -0.0139 1.0000 0.0127
-9.250 -0.9348 0.01732 0.01061 -0.0126 1.0000 0.0131
-9.000 -0.9148 0.01682 0.01008 -0.0113 1.0000 0.0135
-8.750 -0.8947 0.01637 0.00959 -0.0100 1.0000 0.0140
-8.500 -0.8745 0.01593 0.00912 -0.0087 1.0000 0.0146
-8.250 -0.8542 0.01552 0.00868 -0.0073 1.0000 0.0152
-8.000 -0.8337 0.01516 0.00832 -0.0060 1.0000 0.0159
-7.750 -0.8133 0.01482 0.00795 -0.0047 1.0000 0.0167
-7.500 -0.7929 0.01448 0.00758 -0.0033 1.0000 0.0176
-7.250 -0.7618 0.01411 0.00719 -0.0043 0.9978 0.0187
-7.000 -0.7278 0.01376 0.00680 -0.0058 0.9950 0.0203
-6.750 -0.6938 0.01339 0.00642 -0.0073 0.9915 0.0218
-6.500 -0.6590 0.01303 0.00604 -0.0089 0.9870 0.0234
-6.250 -0.6226 0.01271 0.00568 -0.0109 0.9828 0.0248
-6.000 -0.5910 0.01235 0.00532 -0.0118 0.9747 0.0261
-5.750 -0.5586 0.01205 0.00499 -0.0128 0.9672 0.0276
-5.500 -0.5276 0.01178 0.00470 -0.0135 0.9594 0.0291
-5.250 -0.4979 0.01149 0.00442 -0.0140 0.9519 0.0308
-5.000 -0.4681 0.01124 0.00415 -0.0144 0.9432 0.0327
-4.750 -0.4397 0.01100 0.00391 -0.0145 0.9329 0.0352
-4.500 -0.4114 0.01077 0.00368 -0.0145 0.9214 0.0390
-4.250 -0.3842 0.01053 0.00346 -0.0143 0.9076 0.0461
-4.000 -0.3577 0.01031 0.00324 -0.0139 0.8915 0.0557
-3.750 -0.3314 0.01011 0.00304 -0.0135 0.8741 0.0661
-3.500 -0.3054 0.00988 0.00283 -0.0130 0.8562 0.0824
-3.250 -0.2803 0.00954 0.00259 -0.0125 0.8375 0.1192
-3.000 -0.2563 0.00905 0.00235 -0.0118 0.8180 0.1905
-2.750 -0.2314 0.00871 0.00217 -0.0113 0.7979 0.2483
-2.500 -0.2061 0.00843 0.00203 -0.0108 0.7771 0.3008
-2.250 -0.1806 0.00822 0.00192 -0.0103 0.7559 0.3478
-2.000 -0.1548 0.00805 0.00182 -0.0099 0.7336 0.3936
-1.750 -0.1295 0.00784 0.00173 -0.0094 0.7106 0.4432
-1.500 -0.1042 0.00765 0.00166 -0.0089 0.6885 0.4958
-1.000 -0.0531 0.00736 0.00158 -0.0078 0.6477 0.5933
-0.750 -0.0269 0.00729 0.00156 -0.0074 0.6266 0.6282
-0.500 -0.0004 0.00727 0.00154 -0.0070 0.6053 0.6561
-0.250 0.0262 0.00727 0.00154 -0.0066 0.5842 0.6823
0.000 0.0527 0.00727 0.00155 -0.0062 0.5638 0.7083
0.250 0.0794 0.00728 0.00157 -0.0059 0.5452 0.7350
0.500 0.1060 0.00728 0.00160 -0.0055 0.5286 0.7605
0.750 0.1328 0.00731 0.00165 -0.0051 0.5129 0.7842
1.000 0.1595 0.00736 0.00169 -0.0047 0.4945 0.8056
1.250 0.1861 0.00743 0.00175 -0.0043 0.4742 0.8256
1.500 0.2129 0.00750 0.00182 -0.0039 0.4590 0.8446
1.750 0.2400 0.00757 0.00190 -0.0036 0.4470 0.8627
2.000 0.2673 0.00764 0.00199 -0.0033 0.4357 0.8797
2.250 0.2944 0.00775 0.00208 -0.0030 0.4204 0.8957
2.500 0.3217 0.00789 0.00218 -0.0027 0.4024 0.9107
2.750 0.3493 0.00803 0.00228 -0.0025 0.3863 0.9242
3.000 0.3782 0.00821 0.00240 -0.0027 0.3663 0.9345
3.250 0.4072 0.00840 0.00251 -0.0029 0.3431 0.9446
3.500 0.4364 0.00863 0.00263 -0.0032 0.3099 0.9543
3.750 0.4670 0.00899 0.00280 -0.0039 0.2657 0.9617
4.000 0.4940 0.00954 0.00307 -0.0040 0.2029 0.9705
4.250 0.5248 0.01033 0.00348 -0.0052 0.1224 0.9757
4.500 0.5547 0.01088 0.00383 -0.0059 0.0818 0.9821
4.750 0.5885 0.01130 0.00413 -0.0075 0.0615 0.9854
5.000 0.6220 0.01163 0.00440 -0.0089 0.0541 0.9884
5.250 0.6543 0.01194 0.00468 -0.0100 0.0503 0.9918
5.500 0.6866 0.01222 0.00498 -0.0111 0.0480 0.9946
5.750 0.7199 0.01250 0.00527 -0.0125 0.0460 0.9969
6.000 0.7526 0.01284 0.00560 -0.0138 0.0437 0.9994
6.250 0.7761 0.01321 0.00596 -0.0131 0.0416 1.0000
6.500 0.7977 0.01344 0.00623 -0.0120 0.0403 1.0000
6.750 0.8190 0.01371 0.00652 -0.0108 0.0388 1.0000
7.000 0.8402 0.01402 0.00684 -0.0096 0.0373 1.0000
7.250 0.8608 0.01440 0.00721 -0.0084 0.0358 1.0000
7.500 0.8822 0.01471 0.00755 -0.0073 0.0345 1.0000
7.750 0.9039 0.01500 0.00787 -0.0062 0.0330 1.0000
8.000 0.9255 0.01533 0.00821 -0.0051 0.0317 1.0000
8.250 0.9468 0.01571 0.00859 -0.0041 0.0304 1.0000
8.500 0.9684 0.01609 0.00900 -0.0031 0.0293 1.0000
8.750 0.9902 0.01646 0.00941 -0.0022 0.0281 1.0000
9.000 1.0121 0.01683 0.00982 -0.0013 0.0270 1.0000
9.250 1.0337 0.01725 0.01025 -0.0004 0.0260 1.0000
9.500 1.0547 0.01772 0.01075 0.0006 0.0252 1.0000
9.750 1.0756 0.01820 0.01127 0.0015 0.0243 1.0000
10.000 1.0964 0.01867 0.01180 0.0025 0.0235 1.0000
10.250 1.1169 0.01917 0.01232 0.0034 0.0227 1.0000
10.500 1.1366 0.01971 0.01288 0.0044 0.0220 1.0000
10.750 1.1552 0.02032 0.01354 0.0056 0.0213 1.0000
11.000 1.1734 0.02093 0.01423 0.0068 0.0207 1.0000
11.250 1.1910 0.02157 0.01493 0.0081 0.0201 1.0000
11.500 1.2077 0.02223 0.01564 0.0094 0.0195 1.0000
11.750 1.2220 0.02292 0.01639 0.0111 0.0190 1.0000
12.000 1.2340 0.02370 0.01722 0.0130 0.0186 1.0000
12.250 1.2437 0.02467 0.01823 0.0150 0.0181 1.0000
12.500 1.2548 0.02561 0.01927 0.0167 0.0178 1.0000
12.750 1.2649 0.02667 0.02042 0.0183 0.0175 1.0000
13.000 1.2742 0.02785 0.02170 0.0197 0.0171 1.0000
13.250 1.2826 0.02917 0.02311 0.0209 0.0168 1.0000
13.500 1.2902 0.03063 0.02467 0.0219 0.0165 1.0000
13.750 1.2969 0.03227 0.02639 0.0227 0.0162 1.0000
14.000 1.3028 0.03410 0.02832 0.0232 0.0160 1.0000
14.250 1.3073 0.03616 0.03048 0.0234 0.0158 1.0000
14.500 1.3105 0.03850 0.03291 0.0234 0.0156 1.0000
14.750 1.3120 0.04116 0.03567 0.0230 0.0154 1.0000
15.000 1.3114 0.04419 0.03880 0.0224 0.0153 1.0000
15.250 1.3085 0.04761 0.04232 0.0214 0.0151 1.0000
15.500 1.3058 0.05112 0.04594 0.0203 0.0150 1.0000
15.750 1.3028 0.05476 0.04971 0.0191 0.0149 1.0000
16.000 1.2981 0.05868 0.05376 0.0177 0.0148 1.0000
16.250 1.2918 0.06288 0.05810 0.0160 0.0148 1.0000
16.500 1.2841 0.06738 0.06272 0.0142 0.0147 1.0000
16.750 1.2750 0.07216 0.06764 0.0122 0.0146 1.0000
17.000 1.2647 0.07727 0.07288 0.0100 0.0145 1.0000
17.250 1.2534 0.08265 0.07839 0.0075 0.0145 1.0000
17.500 1.2404 0.08841 0.08429 0.0049 0.0144 1.0000
17.750 1.2266 0.09449 0.09050 0.0019 0.0144 1.0000
18.000 1.2115 0.10092 0.09707 -0.0012 0.0143 1.0000
18.250 1.1947 0.10785 0.10414 -0.0047 0.0143 1.0000
18.500 1.1768 0.11521 0.11164 -0.0085 0.0143 1.0000
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