RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 32 MOD AIRFOIL (raf32md-il) Reynolds number: 500,000 Max Cl/Cd: 110.54 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf32md-il-500000-n5.txt Download as CSV file: xf-raf32md-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3962 0.13885 0.13635 -0.0362 1.0000 0.0077
-13.000 -0.3947 0.13502 0.13253 -0.0371 1.0000 0.0078
-11.500 -0.7243 0.03325 0.03030 -0.1033 0.9832 0.0083
-11.250 -0.7089 0.02887 0.02551 -0.1084 0.9784 0.0086
-11.000 -0.6901 0.02602 0.02231 -0.1108 0.9740 0.0089
-10.750 -0.6676 0.02377 0.01978 -0.1128 0.9702 0.0092
-10.500 -0.6395 0.02237 0.01822 -0.1147 0.9683 0.0098
-10.250 -0.6122 0.02160 0.01737 -0.1157 0.9651 0.0103
-10.000 -0.5857 0.02065 0.01626 -0.1165 0.9613 0.0109
-9.750 -0.5570 0.01958 0.01500 -0.1178 0.9586 0.0117
-9.500 -0.5300 0.01846 0.01365 -0.1186 0.9551 0.0123
-9.250 -0.5040 0.01771 0.01282 -0.1190 0.9502 0.0131
-9.000 -0.4729 0.01739 0.01246 -0.1201 0.9472 0.0138
-8.750 -0.4446 0.01697 0.01196 -0.1206 0.9428 0.0147
-8.500 -0.4171 0.01645 0.01132 -0.1209 0.9376 0.0157
-8.250 -0.3867 0.01589 0.01058 -0.1218 0.9340 0.0168
-8.000 -0.3614 0.01541 0.01006 -0.1217 0.9275 0.0177
-7.750 -0.3319 0.01518 0.00978 -0.1223 0.9227 0.0186
-7.500 -0.3046 0.01481 0.00934 -0.1225 0.9170 0.0197
-7.250 -0.2772 0.01447 0.00890 -0.1226 0.9110 0.0210
-7.000 -0.2486 0.01416 0.00846 -0.1229 0.9058 0.0222
-6.750 -0.2221 0.01391 0.00811 -0.1227 0.8990 0.0229
-6.500 -0.1963 0.01306 0.00713 -0.1227 0.8930 0.0242
-6.250 -0.1708 0.01256 0.00658 -0.1225 0.8864 0.0254
-6.000 -0.1440 0.01219 0.00614 -0.1224 0.8800 0.0265
-5.750 -0.1173 0.01184 0.00570 -0.1223 0.8740 0.0276
-5.500 -0.0908 0.01151 0.00530 -0.1221 0.8673 0.0288
-5.250 -0.0638 0.01117 0.00487 -0.1220 0.8615 0.0297
-5.000 -0.0377 0.01086 0.00449 -0.1217 0.8547 0.0304
-4.750 -0.0105 0.01063 0.00417 -0.1216 0.8487 0.0312
-4.500 0.0161 0.01040 0.00388 -0.1214 0.8423 0.0317
-4.250 0.0427 0.01012 0.00352 -0.1212 0.8359 0.0321
-4.000 0.0694 0.00982 0.00313 -0.1210 0.8300 0.0329
-3.750 0.0960 0.00958 0.00283 -0.1208 0.8233 0.0338
-3.250 0.1500 0.00924 0.00237 -0.1204 0.8108 0.0360
-3.000 0.1771 0.00910 0.00218 -0.1202 0.8045 0.0379
-2.750 0.2042 0.00898 0.00202 -0.1200 0.7982 0.0401
-2.500 0.2312 0.00887 0.00188 -0.1198 0.7915 0.0428
-2.250 0.2577 0.00862 0.00174 -0.1196 0.7852 0.0787
-2.000 0.2844 0.00846 0.00166 -0.1194 0.7780 0.1079
-1.750 0.3111 0.00832 0.00157 -0.1192 0.7715 0.1361
-1.500 0.3376 0.00814 0.00150 -0.1190 0.7640 0.1740
-1.250 0.3640 0.00796 0.00147 -0.1188 0.7572 0.2320
-1.000 0.3906 0.00786 0.00145 -0.1186 0.7494 0.2699
-0.750 0.4173 0.00781 0.00144 -0.1184 0.7421 0.2980
-0.500 0.4440 0.00773 0.00144 -0.1182 0.7338 0.3289
-0.250 0.4702 0.00762 0.00144 -0.1179 0.7260 0.3751
0.000 0.4960 0.00745 0.00146 -0.1175 0.7173 0.4358
0.250 0.5209 0.00725 0.00156 -0.1170 0.7090 0.5488
0.500 0.5469 0.00723 0.00160 -0.1166 0.6999 0.5887
0.750 0.5730 0.00722 0.00164 -0.1162 0.6909 0.6184
1.000 0.5986 0.00720 0.00168 -0.1157 0.6819 0.6489
1.250 0.6241 0.00717 0.00174 -0.1151 0.6723 0.6807
1.500 0.6495 0.00717 0.00181 -0.1146 0.6631 0.7111
1.750 0.6739 0.00714 0.00188 -0.1138 0.6537 0.7556
2.000 0.6968 0.00701 0.00196 -0.1126 0.6442 0.8288
2.250 0.7441 0.00691 0.00205 -0.1168 0.6326 1.0000
2.500 0.7690 0.00705 0.00213 -0.1162 0.6196 1.0000
2.750 0.7934 0.00720 0.00222 -0.1154 0.6038 1.0000
3.000 0.8169 0.00739 0.00233 -0.1145 0.5827 1.0000
3.250 0.8397 0.00761 0.00245 -0.1135 0.5594 1.0000
3.500 0.8626 0.00784 0.00258 -0.1125 0.5357 1.0000
3.750 0.8859 0.00806 0.00273 -0.1116 0.5167 1.0000
4.000 0.9085 0.00831 0.00290 -0.1105 0.4917 1.0000
4.250 0.9302 0.00862 0.00310 -0.1094 0.4631 1.0000
4.500 0.9502 0.00901 0.00333 -0.1079 0.4265 1.0000
4.750 0.9692 0.00949 0.00362 -0.1063 0.3838 1.0000
5.000 0.9875 0.01003 0.00395 -0.1046 0.3384 1.0000
5.250 1.0052 0.01062 0.00433 -0.1028 0.2914 1.0000
5.500 1.0209 0.01135 0.00478 -0.1008 0.2355 1.0000
6.000 1.0503 0.01292 0.00582 -0.0964 0.1334 1.0000
6.250 1.0648 0.01369 0.00635 -0.0942 0.0889 1.0000
6.500 1.0820 0.01426 0.00681 -0.0925 0.0689 1.0000
6.750 1.1002 0.01469 0.00722 -0.0908 0.0593 1.0000
7.000 1.1175 0.01513 0.00764 -0.0890 0.0526 1.0000
7.250 1.1358 0.01551 0.00804 -0.0873 0.0477 1.0000
7.500 1.1527 0.01597 0.00850 -0.0855 0.0418 1.0000
7.750 1.1698 0.01642 0.00896 -0.0837 0.0365 1.0000
8.000 1.1855 0.01695 0.00946 -0.0818 0.0296 1.0000
8.250 1.2005 0.01753 0.01001 -0.0798 0.0224 1.0000
8.500 1.2150 0.01815 0.01062 -0.0777 0.0180 1.0000
8.750 1.2297 0.01877 0.01127 -0.0757 0.0157 1.0000
9.000 1.2439 0.01943 0.01197 -0.0737 0.0140 1.0000
9.250 1.2567 0.02019 0.01278 -0.0715 0.0126 1.0000
9.500 1.2694 0.02097 0.01362 -0.0695 0.0117 1.0000
9.750 1.2831 0.02169 0.01441 -0.0676 0.0109 1.0000
10.000 1.2959 0.02249 0.01529 -0.0657 0.0103 1.0000
10.250 1.3079 0.02336 0.01622 -0.0637 0.0097 1.0000
10.500 1.3185 0.02435 0.01727 -0.0617 0.0092 1.0000
10.750 1.3263 0.02558 0.01857 -0.0594 0.0086 1.0000
11.000 1.3353 0.02675 0.01982 -0.0574 0.0083 1.0000
11.250 1.3452 0.02787 0.02106 -0.0556 0.0081 1.0000
11.500 1.3541 0.02911 0.02239 -0.0538 0.0078 1.0000
11.750 1.3627 0.03041 0.02378 -0.0521 0.0075 1.0000
12.000 1.3707 0.03179 0.02524 -0.0504 0.0072 1.0000
12.250 1.3798 0.03310 0.02663 -0.0490 0.0069 1.0000
12.500 1.3869 0.03463 0.02824 -0.0475 0.0066 1.0000
12.750 1.3932 0.03626 0.02995 -0.0461 0.0064 1.0000
13.000 1.3966 0.03821 0.03199 -0.0446 0.0062 1.0000
13.250 1.3954 0.04069 0.03457 -0.0430 0.0060 1.0000
13.500 1.4001 0.04265 0.03664 -0.0419 0.0059 1.0000
13.750 1.4035 0.04480 0.03894 -0.0409 0.0058 1.0000
14.000 1.4056 0.04717 0.04144 -0.0400 0.0057 1.0000
14.250 1.4073 0.04967 0.04407 -0.0392 0.0056 1.0000
14.500 1.4077 0.05240 0.04693 -0.0386 0.0055 1.0000
14.750 1.4078 0.05525 0.04991 -0.0382 0.0053 1.0000
15.000 1.4060 0.05844 0.05324 -0.0380 0.0052 1.0000
15.250 1.4050 0.06165 0.05658 -0.0380 0.0051 1.0000
15.500 1.4021 0.06520 0.06027 -0.0382 0.0050 1.0000
15.750 1.3975 0.06913 0.06434 -0.0387 0.0050 1.0000
16.000 1.3942 0.07303 0.06837 -0.0395 0.0049 1.0000
16.250 1.3877 0.07752 0.07301 -0.0405 0.0048 1.0000
16.500 1.3823 0.08199 0.07762 -0.0418 0.0047 1.0000
16.750 1.3740 0.08708 0.08286 -0.0434 0.0047 1.0000
17.000 1.3663 0.09228 0.08820 -0.0454 0.0046 1.0000
17.250 1.3561 0.09807 0.09414 -0.0477 0.0046 1.0000
17.500 1.3445 0.10428 0.10051 -0.0505 0.0046 1.0000
17.750 1.3342 0.11051 0.10688 -0.0535 0.0045 1.0000
18.000 1.3208 0.11755 0.11407 -0.0571 0.0045 1.0000
18.250 1.3096 0.12436 0.12102 -0.0608 0.0045 1.0000
18.500 1.2943 0.13220 0.12902 -0.0652 0.0045 1.0000
18.750 1.2809 0.13992 0.13688 -0.0698 0.0045 1.0000
19.000 1.2655 0.14838 0.14550 -0.0749 0.0045 1.0000
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Polar data table (+)
Polar graphs
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