RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 32 MOD AIRFOIL (raf32md-il) Reynolds number: 200,000 Max Cl/Cd: 83.79 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf32md-il-200000-n5.txt Download as CSV file: xf-raf32md-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3926 0.09621 0.09271 -0.0432 1.0000 0.0187
-9.500 -0.3999 0.09353 0.09009 -0.0423 1.0000 0.0192
-9.250 -0.3990 0.08905 0.08564 -0.0452 0.9981 0.0197
-9.000 -0.3943 0.08260 0.07921 -0.0515 0.9937 0.0204
-8.750 -0.3928 0.07529 0.07192 -0.0589 0.9876 0.0206
-8.500 -0.3971 0.06632 0.06298 -0.0688 0.9783 0.0206
-8.250 -0.4214 0.03847 0.03432 -0.1015 0.9592 0.0204
-8.000 -0.4085 0.03229 0.02737 -0.1057 0.9517 0.0216
-7.750 -0.3822 0.02935 0.02373 -0.1082 0.9477 0.0231
-7.500 -0.3585 0.02667 0.02086 -0.1097 0.9436 0.0246
-7.250 -0.3331 0.02534 0.01934 -0.1104 0.9385 0.0259
-7.000 -0.3030 0.02369 0.01738 -0.1119 0.9355 0.0275
-6.750 -0.2742 0.02250 0.01588 -0.1128 0.9318 0.0297
-6.500 -0.2484 0.02155 0.01464 -0.1127 0.9262 0.0312
-6.000 -0.1886 0.01865 0.01136 -0.1148 0.9199 0.0349
-5.750 -0.1648 0.01791 0.01052 -0.1142 0.9134 0.0366
-5.500 -0.1344 0.01707 0.00955 -0.1149 0.9096 0.0380
-5.250 -0.1020 0.01635 0.00870 -0.1160 0.9069 0.0400
-5.000 -0.0785 0.01584 0.00809 -0.1152 0.8999 0.0415
-4.750 -0.0486 0.01525 0.00738 -0.1157 0.8955 0.0425
-4.500 -0.0170 0.01460 0.00665 -0.1166 0.8923 0.0436
-4.250 0.0069 0.01413 0.00613 -0.1159 0.8851 0.0452
-4.000 0.0365 0.01370 0.00563 -0.1163 0.8803 0.0474
-3.750 0.0676 0.01332 0.00518 -0.1170 0.8763 0.0510
-3.500 0.0930 0.01307 0.00486 -0.1165 0.8693 0.0542
-3.250 0.1229 0.01271 0.00451 -0.1169 0.8644 0.0621
-3.000 0.1507 0.01237 0.00425 -0.1170 0.8587 0.0902
-2.750 0.1780 0.01209 0.00403 -0.1169 0.8523 0.1228
-2.500 0.2081 0.01173 0.00379 -0.1175 0.8477 0.1648
-2.250 0.2330 0.01147 0.00370 -0.1170 0.8403 0.2170
-2.000 0.2616 0.01123 0.00360 -0.1172 0.8346 0.2746
-1.750 0.2888 0.01109 0.00352 -0.1171 0.8281 0.3118
-1.500 0.3158 0.01092 0.00345 -0.1169 0.8213 0.3550
-1.250 0.3435 0.01069 0.00338 -0.1169 0.8154 0.4080
-1.000 0.3681 0.01046 0.00341 -0.1163 0.8078 0.4744
-0.500 0.4204 0.01023 0.00344 -0.1154 0.7939 0.5995
-0.250 0.4472 0.01007 0.00340 -0.1149 0.7876 0.6519
0.000 0.4707 0.00993 0.00345 -0.1138 0.7794 0.7050
0.250 0.4972 0.00977 0.00342 -0.1132 0.7728 0.7633
0.500 0.5234 0.00961 0.00345 -0.1126 0.7647 0.8341
0.750 0.5757 0.00944 0.00336 -0.1176 0.7583 1.0000
1.000 0.6013 0.00953 0.00340 -0.1171 0.7495 1.0000
1.250 0.6287 0.00960 0.00340 -0.1169 0.7419 1.0000
1.500 0.6542 0.00969 0.00346 -0.1165 0.7327 1.0000
1.750 0.6807 0.00979 0.00352 -0.1161 0.7243 1.0000
2.000 0.7070 0.00988 0.00358 -0.1158 0.7154 1.0000
2.250 0.7329 0.00999 0.00367 -0.1153 0.7062 1.0000
2.500 0.7596 0.01010 0.00374 -0.1150 0.6975 1.0000
2.750 0.7849 0.01022 0.00387 -0.1145 0.6875 1.0000
3.000 0.8108 0.01035 0.00399 -0.1140 0.6779 1.0000
3.500 0.8617 0.01062 0.00424 -0.1129 0.6552 1.0000
3.750 0.8859 0.01078 0.00435 -0.1120 0.6392 1.0000
4.000 0.9087 0.01095 0.00448 -0.1109 0.6179 1.0000
4.250 0.9312 0.01116 0.00463 -0.1097 0.5956 1.0000
4.500 0.9535 0.01138 0.00480 -0.1085 0.5734 1.0000
4.750 0.9753 0.01164 0.00500 -0.1072 0.5499 1.0000
5.000 0.9967 0.01191 0.00524 -0.1059 0.5257 1.0000
5.250 1.0163 0.01226 0.00550 -0.1043 0.4944 1.0000
5.500 1.0346 0.01266 0.00579 -0.1024 0.4600 1.0000
5.750 1.0512 0.01316 0.00614 -0.1003 0.4192 1.0000
6.000 1.0657 0.01377 0.00656 -0.0979 0.3733 1.0000
6.250 1.0775 0.01453 0.00710 -0.0951 0.3201 1.0000
6.500 1.0864 0.01550 0.00775 -0.0919 0.2585 1.0000
6.750 1.0927 0.01665 0.00854 -0.0885 0.1946 1.0000
7.000 1.0992 0.01773 0.00933 -0.0851 0.1454 1.0000
7.250 1.1071 0.01876 0.01011 -0.0820 0.1039 1.0000
7.500 1.1169 0.01970 0.01089 -0.0792 0.0802 1.0000
7.750 1.1295 0.02050 0.01166 -0.0769 0.0683 1.0000
8.000 1.1428 0.02125 0.01247 -0.0748 0.0600 1.0000
8.250 1.1550 0.02210 0.01332 -0.0726 0.0524 1.0000
8.500 1.1686 0.02287 0.01417 -0.0706 0.0458 1.0000
8.750 1.1797 0.02383 0.01511 -0.0684 0.0391 1.0000
9.000 1.1923 0.02470 0.01604 -0.0664 0.0327 1.0000
9.250 1.2030 0.02574 0.01712 -0.0643 0.0283 1.0000
9.500 1.2131 0.02683 0.01828 -0.0622 0.0250 1.0000
9.750 1.2210 0.02812 0.01962 -0.0599 0.0227 1.0000
10.000 1.2310 0.02929 0.02089 -0.0580 0.0206 1.0000
10.250 1.2401 0.03056 0.02224 -0.0561 0.0190 1.0000
10.500 1.2469 0.03205 0.02380 -0.0541 0.0177 1.0000
10.750 1.2505 0.03389 0.02572 -0.0519 0.0168 1.0000
11.000 1.2577 0.03548 0.02745 -0.0501 0.0161 1.0000
11.250 1.2642 0.03722 0.02932 -0.0484 0.0155 1.0000
11.500 1.2710 0.03897 0.03120 -0.0468 0.0148 1.0000
11.750 1.2777 0.04076 0.03311 -0.0453 0.0141 1.0000
12.000 1.2842 0.04259 0.03508 -0.0440 0.0134 1.0000
12.250 1.2894 0.04456 0.03715 -0.0428 0.0129 1.0000
12.500 1.2919 0.04694 0.03962 -0.0416 0.0123 1.0000
12.750 1.2936 0.04963 0.04243 -0.0403 0.0119 1.0000
13.000 1.2982 0.05197 0.04497 -0.0392 0.0117 1.0000
13.250 1.3015 0.05455 0.04775 -0.0383 0.0114 1.0000
13.500 1.3034 0.05734 0.05074 -0.0374 0.0112 1.0000
13.750 1.3037 0.06038 0.05399 -0.0368 0.0110 1.0000
14.000 1.3020 0.06371 0.05754 -0.0363 0.0108 1.0000
14.250 1.2984 0.06738 0.06143 -0.0361 0.0106 1.0000
14.500 1.2930 0.07136 0.06564 -0.0362 0.0104 1.0000
14.750 1.2859 0.07565 0.07014 -0.0367 0.0102 1.0000
15.000 1.2770 0.08041 0.07513 -0.0377 0.0101 1.0000
15.250 1.2675 0.08539 0.08032 -0.0391 0.0099 1.0000
15.500 1.2566 0.09083 0.08595 -0.0409 0.0097 1.0000
15.750 1.2422 0.09718 0.09253 -0.0434 0.0097 1.0000
16.000 1.2298 0.10342 0.09896 -0.0464 0.0096 1.0000
16.250 1.2117 0.11122 0.10699 -0.0503 0.0096 1.0000
16.500 1.1949 0.11917 0.11514 -0.0548 0.0096 1.0000
16.750 1.1712 0.12934 0.12556 -0.0609 0.0097 1.0000
17.000 1.1429 0.14175 0.13820 -0.0688 0.0099 1.0000
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