RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 32 MOD AIRFOIL (raf32md-il) Reynolds number: 100,000 Max Cl/Cd: 61.33 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf32md-il-100000-n5.txt Download as CSV file: xf-raf32md-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3984 0.09219 0.08745 -0.0414 1.0000 0.0367
-8.500 -0.4118 0.08954 0.08488 -0.0400 1.0000 0.0364
-8.250 -0.4280 0.08711 0.08255 -0.0382 1.0000 0.0362
-8.000 -0.4329 0.08297 0.07847 -0.0409 0.9962 0.0363
-7.750 -0.4265 0.07578 0.07129 -0.0498 0.9880 0.0359
-7.500 -0.4165 0.06470 0.06015 -0.0646 0.9785 0.0353
-7.250 -0.4108 0.04953 0.04448 -0.0815 0.9683 0.0348
-7.000 -0.3949 0.04354 0.03800 -0.0867 0.9607 0.0358
-6.750 -0.3705 0.03898 0.03286 -0.0908 0.9558 0.0384
-6.500 -0.3489 0.03471 0.02789 -0.0930 0.9494 0.0402
-6.250 -0.3184 0.03128 0.02371 -0.0955 0.9460 0.0419
-6.000 -0.2959 0.02904 0.02109 -0.0958 0.9398 0.0443
-5.750 -0.2656 0.02739 0.01922 -0.0971 0.9360 0.0465
-5.500 -0.2342 0.02584 0.01736 -0.0983 0.9325 0.0484
-5.250 -0.2089 0.02479 0.01603 -0.0982 0.9263 0.0515
-5.000 -0.1761 0.02363 0.01458 -0.0994 0.9229 0.0540
-4.750 -0.1440 0.02247 0.01328 -0.1004 0.9196 0.0556
-4.500 -0.1201 0.02168 0.01246 -0.0999 0.9130 0.0576
-4.250 -0.0871 0.02098 0.01167 -0.1011 0.9093 0.0611
-4.000 -0.0512 0.02034 0.01088 -0.1028 0.9068 0.0663
-3.750 -0.0299 0.01985 0.01038 -0.1017 0.8989 0.0701
-3.500 0.0035 0.01929 0.00973 -0.1029 0.8952 0.0769
-3.250 0.0396 0.01867 0.00910 -0.1045 0.8925 0.0927
-3.000 0.0618 0.01826 0.00877 -0.1036 0.8847 0.1214
-2.750 0.0941 0.01772 0.00837 -0.1047 0.8805 0.1685
-2.500 0.1286 0.01717 0.00815 -0.1062 0.8775 0.2537
-2.250 0.1513 0.01700 0.00814 -0.1054 0.8695 0.3184
-2.000 0.1838 0.01668 0.00792 -0.1064 0.8652 0.3728
-1.750 0.2175 0.01628 0.00771 -0.1074 0.8619 0.4332
-1.500 0.2384 0.01613 0.00781 -0.1060 0.8535 0.4990
-1.250 0.2709 0.01589 0.00766 -0.1066 0.8493 0.5702
-1.000 0.2970 0.01576 0.00762 -0.1061 0.8427 0.6256
-0.750 0.3235 0.01548 0.00755 -0.1053 0.8368 0.6964
-0.500 0.3548 0.01502 0.00735 -0.1052 0.8330 0.7962
-0.250 0.4021 0.01474 0.00724 -0.1089 0.8270 1.0000
0.000 0.4328 0.01475 0.00710 -0.1095 0.8208 1.0000
0.250 0.4640 0.01475 0.00698 -0.1101 0.8151 1.0000
0.500 0.4900 0.01485 0.00700 -0.1097 0.8070 1.0000
0.750 0.5243 0.01479 0.00684 -0.1108 0.8023 1.0000
1.000 0.5470 0.01497 0.00697 -0.1099 0.7929 1.0000
1.250 0.5801 0.01494 0.00687 -0.1107 0.7877 1.0000
1.500 0.6033 0.01512 0.00703 -0.1099 0.7783 1.0000
1.750 0.6359 0.01509 0.00695 -0.1106 0.7727 1.0000
2.000 0.6589 0.01529 0.00716 -0.1097 0.7630 1.0000
2.250 0.6906 0.01529 0.00713 -0.1102 0.7568 1.0000
2.750 0.7421 0.01557 0.00745 -0.1093 0.7393 1.0000
3.000 0.7689 0.01568 0.00759 -0.1089 0.7307 1.0000
3.250 0.7944 0.01584 0.00778 -0.1084 0.7215 1.0000
3.500 0.8242 0.01588 0.00787 -0.1086 0.7137 1.0000
3.750 0.8476 0.01610 0.00815 -0.1077 0.7032 1.0000
4.000 0.8746 0.01622 0.00833 -0.1073 0.6939 1.0000
4.250 0.9025 0.01630 0.00847 -0.1071 0.6842 1.0000
4.500 0.9269 0.01642 0.00866 -0.1062 0.6706 1.0000
4.750 0.9526 0.01643 0.00869 -0.1053 0.6539 1.0000
5.000 0.9747 0.01652 0.00882 -0.1039 0.6333 1.0000
5.250 0.9978 0.01662 0.00896 -0.1026 0.6120 1.0000
5.500 1.0190 0.01676 0.00910 -0.1009 0.5863 1.0000
5.750 1.0387 0.01696 0.00927 -0.0990 0.5565 1.0000
6.000 1.0573 0.01724 0.00952 -0.0970 0.5241 1.0000
6.250 1.0757 0.01760 0.00988 -0.0951 0.4918 1.0000
6.500 1.0923 0.01805 0.01026 -0.0928 0.4533 1.0000
6.750 1.1051 0.01869 0.01071 -0.0900 0.4015 1.0000
7.000 1.1130 0.01961 0.01131 -0.0866 0.3371 1.0000
7.250 1.1169 0.02083 0.01214 -0.0827 0.2678 1.0000
7.500 1.1174 0.02224 0.01316 -0.0786 0.2054 1.0000
7.750 1.1196 0.02371 0.01431 -0.0749 0.1565 1.0000
8.000 1.1236 0.02515 0.01553 -0.0716 0.1195 1.0000
8.250 1.1300 0.02649 0.01671 -0.0688 0.0957 1.0000
8.500 1.1368 0.02781 0.01796 -0.0661 0.0808 1.0000
8.750 1.1449 0.02909 0.01927 -0.0637 0.0704 1.0000
9.000 1.1506 0.03058 0.02075 -0.0611 0.0620 1.0000
9.250 1.1582 0.03198 0.02226 -0.0588 0.0545 1.0000
9.500 1.1628 0.03368 0.02399 -0.0563 0.0483 1.0000
9.750 1.1708 0.03518 0.02560 -0.0543 0.0427 1.0000
10.000 1.1744 0.03712 0.02757 -0.0521 0.0394 1.0000
10.250 1.1840 0.03873 0.02937 -0.0503 0.0359 1.0000
10.500 1.1923 0.04034 0.03106 -0.0487 0.0328 1.0000
10.750 1.1983 0.04230 0.03301 -0.0471 0.0307 1.0000
11.000 1.2098 0.04414 0.03507 -0.0455 0.0288 1.0000
11.250 1.2213 0.04610 0.03720 -0.0441 0.0271 1.0000
11.500 1.2304 0.04801 0.03924 -0.0428 0.0255 1.0000
11.750 1.2375 0.05004 0.04134 -0.0417 0.0243 1.0000
12.000 1.2450 0.05241 0.04380 -0.0405 0.0231 1.0000
12.250 1.2543 0.05493 0.04668 -0.0393 0.0221 1.0000
12.500 1.2610 0.05785 0.04990 -0.0380 0.0214 1.0000
12.750 1.2638 0.06105 0.05340 -0.0369 0.0208 1.0000
13.000 1.2627 0.06457 0.05721 -0.0358 0.0204 1.0000
13.250 1.2575 0.06837 0.06130 -0.0350 0.0200 1.0000
13.500 1.2495 0.07241 0.06562 -0.0346 0.0196 1.0000
13.750 1.2392 0.07674 0.07021 -0.0346 0.0193 1.0000
14.000 1.2264 0.08154 0.07527 -0.0351 0.0191 1.0000
14.250 1.2119 0.08673 0.08071 -0.0362 0.0189 1.0000
14.500 1.1958 0.09246 0.08668 -0.0379 0.0187 1.0000
14.750 1.1769 0.09905 0.09351 -0.0406 0.0187 1.0000
15.000 1.1548 0.10679 0.10151 -0.0443 0.0188 1.0000
15.250 1.1268 0.11659 0.11157 -0.0499 0.0191 1.0000
15.500 1.0889 0.13023 0.12547 -0.0586 0.0200 1.0000
15.750 1.0515 0.14645 0.14179 -0.0693 0.0209 1.0000
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