RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 32 MOD AIRFOIL (raf32md-il) Reynolds number: 200,000 Max Cl/Cd: 87.25 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf32md-il-200000.txt Download as CSV file: xf-raf32md-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 32 MOD AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4122 0.09903 0.09571 -0.0414 1.0000 0.0576
-8.750 -0.4330 0.09715 0.09393 -0.0401 1.0000 0.0578
-8.500 -0.4534 0.09565 0.09252 -0.0380 1.0000 0.0579
-8.000 -0.4356 0.09056 0.08743 -0.0303 1.0000 0.0614
-7.750 -0.4397 0.08857 0.08548 -0.0295 0.9990 0.0629
-7.500 -0.4288 0.08405 0.08095 -0.0366 0.9932 0.0669
-7.250 -0.4136 0.07070 0.06755 -0.0622 0.9825 0.0714
-7.000 -0.3959 0.07010 0.06696 -0.0583 0.9786 0.0732
-6.750 -0.3663 0.06175 0.05837 -0.0748 0.9718 0.0821
-6.500 -0.3552 0.05491 0.05137 -0.0804 0.9642 0.0853
-6.250 -0.3291 0.05370 0.05022 -0.0803 0.9608 0.0886
-6.000 -0.3111 0.03349 0.02828 -0.0932 0.9531 0.0557
-5.750 -0.2861 0.02862 0.02280 -0.0946 0.9482 0.0525
-5.500 -0.2520 0.02586 0.01952 -0.0966 0.9452 0.0535
-5.250 -0.2148 0.02370 0.01691 -0.0988 0.9432 0.0547
-5.000 -0.1917 0.02228 0.01517 -0.0980 0.9366 0.0553
-4.750 -0.1577 0.02118 0.01379 -0.0992 0.9328 0.0572
-4.500 -0.1210 0.01969 0.01212 -0.1010 0.9305 0.0592
-4.250 -0.0825 0.01851 0.01090 -0.1032 0.9286 0.0614
-4.000 -0.0607 0.01796 0.01033 -0.1020 0.9210 0.0637
-3.750 -0.0246 0.01735 0.00967 -0.1037 0.9177 0.0679
-3.500 0.0142 0.01653 0.00883 -0.1058 0.9155 0.0722
-3.250 0.0554 0.01588 0.00819 -0.1084 0.9139 0.0802
-3.000 0.0759 0.01552 0.00786 -0.1070 0.9054 0.0925
-2.750 0.1126 0.01442 0.00728 -0.1091 0.9026 0.1996
-2.500 0.1514 0.01388 0.00704 -0.1114 0.9004 0.3052
-2.250 0.1773 0.01369 0.00696 -0.1110 0.8937 0.3548
-2.000 0.2098 0.01334 0.00676 -0.1119 0.8891 0.4071
-1.750 0.2459 0.01286 0.00652 -0.1134 0.8862 0.4718
-1.500 0.2709 0.01265 0.00657 -0.1126 0.8795 0.5577
-1.250 0.3006 0.01236 0.00645 -0.1127 0.8742 0.6272
-1.000 0.3335 0.01193 0.00623 -0.1131 0.8709 0.6989
-0.750 0.3542 0.01174 0.00624 -0.1112 0.8628 0.7632
-0.500 0.3889 0.01128 0.00602 -0.1118 0.8585 0.8571
-0.250 0.4568 0.01091 0.00567 -0.1200 0.8568 1.0000
0.000 0.4818 0.01097 0.00563 -0.1194 0.8484 1.0000
0.250 0.5138 0.01088 0.00545 -0.1200 0.8426 1.0000
0.500 0.5398 0.01094 0.00544 -0.1196 0.8345 1.0000
0.750 0.5703 0.01089 0.00531 -0.1199 0.8280 1.0000
1.000 0.5962 0.01096 0.00533 -0.1194 0.8196 1.0000
1.250 0.6264 0.01093 0.00525 -0.1196 0.8128 1.0000
1.500 0.6515 0.01103 0.00532 -0.1189 0.8038 1.0000
1.750 0.6822 0.01101 0.00524 -0.1193 0.7971 1.0000
2.000 0.7062 0.01113 0.00536 -0.1184 0.7874 1.0000
2.250 0.7364 0.01114 0.00533 -0.1186 0.7803 1.0000
2.500 0.7608 0.01125 0.00544 -0.1178 0.7704 1.0000
2.750 0.7874 0.01133 0.00554 -0.1174 0.7615 1.0000
3.000 0.8158 0.01137 0.00556 -0.1173 0.7531 1.0000
3.250 0.8401 0.01148 0.00569 -0.1164 0.7424 1.0000
3.500 0.8661 0.01151 0.00572 -0.1158 0.7310 1.0000
3.750 0.8918 0.01150 0.00571 -0.1149 0.7173 1.0000
4.000 0.9162 0.01147 0.00567 -0.1138 0.7012 1.0000
4.250 0.9402 0.01148 0.00566 -0.1127 0.6844 1.0000
4.500 0.9643 0.01154 0.00573 -0.1116 0.6680 1.0000
4.750 0.9883 0.01163 0.00579 -0.1105 0.6506 1.0000
5.000 1.0107 0.01175 0.00591 -0.1091 0.6308 1.0000
5.250 1.0326 0.01190 0.00606 -0.1077 0.6095 1.0000
5.500 1.0546 0.01210 0.00625 -0.1063 0.5885 1.0000
5.750 1.0749 0.01232 0.00648 -0.1046 0.5640 1.0000
6.000 1.0935 0.01259 0.00671 -0.1026 0.5333 1.0000
6.250 1.1087 0.01298 0.00696 -0.1000 0.4895 1.0000
6.500 1.1183 0.01362 0.00731 -0.0964 0.4252 1.0000
6.750 1.1201 0.01470 0.00791 -0.0917 0.3350 1.0000
7.000 1.1146 0.01634 0.00886 -0.0862 0.2262 1.0000
7.250 1.1100 0.01801 0.00997 -0.0810 0.1448 1.0000
7.500 1.1121 0.01939 0.01103 -0.0769 0.1028 1.0000
7.750 1.1166 0.02065 0.01214 -0.0733 0.0846 1.0000
8.000 1.1229 0.02186 0.01331 -0.0700 0.0726 1.0000
8.250 1.1312 0.02302 0.01451 -0.0671 0.0634 1.0000
8.500 1.1362 0.02449 0.01601 -0.0639 0.0564 1.0000
8.750 1.1447 0.02577 0.01729 -0.0614 0.0503 1.0000
9.000 1.1531 0.02738 0.01892 -0.0589 0.0461 1.0000
9.250 1.1665 0.02863 0.02025 -0.0570 0.0429 1.0000
9.500 1.1797 0.03001 0.02162 -0.0553 0.0399 1.0000
9.750 1.1984 0.03187 0.02351 -0.0542 0.0369 1.0000
10.000 1.2163 0.03313 0.02492 -0.0529 0.0347 1.0000
10.250 1.2361 0.03463 0.02652 -0.0520 0.0329 1.0000
10.500 1.2570 0.03630 0.02826 -0.0513 0.0315 1.0000
10.750 1.2996 0.04031 0.03239 -0.0538 0.0296 1.0000
11.000 1.3035 0.04145 0.03380 -0.0507 0.0287 1.0000
11.250 1.3134 0.04348 0.03613 -0.0487 0.0278 1.0000
11.500 1.3228 0.04618 0.03915 -0.0468 0.0272 1.0000
11.750 1.3270 0.04921 0.04250 -0.0445 0.0269 1.0000
12.000 1.3255 0.05244 0.04605 -0.0418 0.0267 1.0000
12.250 1.3194 0.05600 0.04994 -0.0391 0.0268 1.0000
12.500 1.3084 0.05983 0.05408 -0.0365 0.0269 1.0000
12.750 1.2935 0.06392 0.05847 -0.0342 0.0271 1.0000
13.000 1.2760 0.06833 0.06316 -0.0324 0.0274 1.0000
13.250 1.2567 0.07306 0.06815 -0.0312 0.0277 1.0000
13.500 1.2361 0.07812 0.07343 -0.0309 0.0279 1.0000
13.750 1.2140 0.08366 0.07919 -0.0313 0.0282 1.0000
14.000 1.1918 0.08960 0.08532 -0.0326 0.0284 1.0000
14.250 1.1698 0.09605 0.09194 -0.0347 0.0288 1.0000
14.500 1.1466 0.10315 0.09920 -0.0376 0.0290 1.0000
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Polar data table (+)
Polar graphs
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