RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 32 MOD AIRFOIL (raf32md-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.34 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf32md-il-1000000-n5.txt Download as CSV file: xf-raf32md-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.4387 0.15191 0.15011 -0.0310 1.0000 0.0044
-14.500 -0.4386 0.14735 0.14556 -0.0323 1.0000 0.0046
-13.500 -0.9078 0.03364 0.03110 -0.1028 0.9929 0.0049
-13.250 -0.8959 0.02914 0.02632 -0.1091 0.9883 0.0050
-13.000 -0.8753 0.02651 0.02349 -0.1126 0.9862 0.0052
-12.750 -0.8572 0.02466 0.02149 -0.1138 0.9819 0.0054
-12.500 -0.8338 0.02302 0.01969 -0.1155 0.9795 0.0055
-12.250 -0.8074 0.02172 0.01825 -0.1172 0.9779 0.0058
-12.000 -0.7828 0.02046 0.01684 -0.1183 0.9752 0.0060
-11.750 -0.7577 0.01938 0.01562 -0.1192 0.9718 0.0062
-11.500 -0.7302 0.01839 0.01449 -0.1203 0.9694 0.0064
-11.250 -0.7010 0.01748 0.01343 -0.1217 0.9675 0.0065
-11.000 -0.6781 0.01645 0.01228 -0.1218 0.9622 0.0070
-10.750 -0.6500 0.01565 0.01139 -0.1227 0.9588 0.0073
-10.500 -0.6228 0.01498 0.01063 -0.1232 0.9549 0.0078
-10.250 -0.5966 0.01437 0.00993 -0.1235 0.9496 0.0082
-10.000 -0.5682 0.01380 0.00925 -0.1241 0.9455 0.0086
-9.750 -0.5430 0.01331 0.00865 -0.1239 0.9389 0.0090
-9.500 -0.5157 0.01277 0.00803 -0.1242 0.9333 0.0098
-9.250 -0.4903 0.01236 0.00757 -0.1241 0.9260 0.0106
-9.000 -0.4633 0.01200 0.00714 -0.1241 0.9196 0.0117
-8.750 -0.4375 0.01165 0.00672 -0.1239 0.9122 0.0124
-8.500 -0.4107 0.01138 0.00641 -0.1239 0.9056 0.0137
-8.250 -0.3840 0.01119 0.00621 -0.1238 0.8982 0.0148
-8.000 -0.3572 0.01100 0.00595 -0.1237 0.8913 0.0159
-7.750 -0.3308 0.01078 0.00567 -0.1235 0.8840 0.0166
-7.500 -0.3043 0.01055 0.00538 -0.1233 0.8770 0.0176
-7.250 -0.2774 0.01043 0.00526 -0.1232 0.8700 0.0186
-7.000 -0.2504 0.01032 0.00510 -0.1231 0.8630 0.0195
-6.750 -0.2237 0.01015 0.00488 -0.1229 0.8565 0.0204
-6.500 -0.1969 0.01002 0.00469 -0.1228 0.8497 0.0214
-6.250 -0.1699 0.00988 0.00450 -0.1226 0.8435 0.0222
-6.000 -0.1431 0.00975 0.00432 -0.1225 0.8367 0.0226
-5.750 -0.1160 0.00967 0.00417 -0.1223 0.8309 0.0230
-5.500 -0.0899 0.00934 0.00377 -0.1221 0.8245 0.0236
-5.250 -0.0642 0.00894 0.00329 -0.1218 0.8183 0.0249
-5.000 -0.0375 0.00871 0.00302 -0.1216 0.8124 0.0259
-4.750 -0.0108 0.00852 0.00277 -0.1214 0.8060 0.0266
-4.500 0.0161 0.00837 0.00257 -0.1212 0.8003 0.0274
-4.250 0.0432 0.00821 0.00237 -0.1210 0.7940 0.0280
-4.000 0.0700 0.00808 0.00218 -0.1208 0.7879 0.0284
-3.750 0.0973 0.00794 0.00200 -0.1207 0.7818 0.0289
-3.500 0.1243 0.00783 0.00184 -0.1205 0.7752 0.0293
-3.250 0.1515 0.00773 0.00169 -0.1204 0.7692 0.0297
-3.000 0.1787 0.00763 0.00156 -0.1202 0.7622 0.0301
-2.750 0.2058 0.00756 0.00144 -0.1200 0.7557 0.0306
-2.500 0.2331 0.00749 0.00134 -0.1199 0.7483 0.0312
-2.250 0.2601 0.00744 0.00125 -0.1197 0.7414 0.0317
-2.000 0.2874 0.00737 0.00116 -0.1195 0.7336 0.0342
-1.750 0.3143 0.00731 0.00109 -0.1193 0.7261 0.0395
-1.500 0.3407 0.00708 0.00101 -0.1191 0.7176 0.0888
-1.250 0.3674 0.00701 0.00097 -0.1189 0.7092 0.1088
-1.000 0.3941 0.00694 0.00093 -0.1186 0.7003 0.1308
-0.750 0.4206 0.00681 0.00090 -0.1184 0.6916 0.1712
-0.500 0.4466 0.00668 0.00090 -0.1181 0.6825 0.2269
-0.250 0.4732 0.00662 0.00091 -0.1179 0.6731 0.2630
0.000 0.4997 0.00658 0.00093 -0.1177 0.6639 0.2936
0.250 0.5261 0.00657 0.00096 -0.1174 0.6544 0.3230
0.500 0.5527 0.00653 0.00099 -0.1172 0.6453 0.3531
0.750 0.5787 0.00647 0.00102 -0.1169 0.6359 0.4003
1.000 0.6037 0.00625 0.00111 -0.1164 0.6266 0.5157
1.250 0.6298 0.00624 0.00118 -0.1161 0.6174 0.5647
1.500 0.6557 0.00628 0.00125 -0.1157 0.6070 0.5934
1.750 0.6813 0.00633 0.00133 -0.1152 0.5937 0.6168
2.000 0.7069 0.00642 0.00140 -0.1148 0.5790 0.6311
2.250 0.7323 0.00650 0.00148 -0.1143 0.5641 0.6474
2.500 0.7564 0.00663 0.00158 -0.1135 0.5396 0.6710
2.750 0.7794 0.00675 0.00171 -0.1125 0.5135 0.7090
3.000 0.8016 0.00687 0.00185 -0.1114 0.4868 0.7597
3.250 0.8236 0.00685 0.00198 -0.1102 0.4695 0.8304
3.500 0.8629 0.00694 0.00219 -0.1129 0.4324 1.0000
3.750 0.8841 0.00733 0.00239 -0.1117 0.3914 1.0000
4.000 0.9061 0.00769 0.00260 -0.1106 0.3576 1.0000
4.250 0.9263 0.00816 0.00286 -0.1092 0.3125 1.0000
4.500 0.9448 0.00875 0.00319 -0.1076 0.2578 1.0000
4.750 0.9641 0.00928 0.00351 -0.1061 0.2130 1.0000
5.000 0.9833 0.00981 0.00384 -0.1046 0.1729 1.0000
5.250 1.0023 0.01036 0.00420 -0.1031 0.1346 1.0000
5.500 1.0192 0.01103 0.00461 -0.1012 0.0867 1.0000
5.750 1.0389 0.01149 0.00496 -0.0998 0.0639 1.0000
6.000 1.0610 0.01179 0.00523 -0.0988 0.0569 1.0000
6.250 1.0826 0.01211 0.00553 -0.0977 0.0496 1.0000
6.500 1.1045 0.01240 0.00581 -0.0967 0.0452 1.0000
6.750 1.1252 0.01274 0.00613 -0.0955 0.0397 1.0000
7.000 1.1463 0.01305 0.00643 -0.0943 0.0353 1.0000
7.250 1.1654 0.01342 0.00676 -0.0928 0.0294 1.0000
7.500 1.1824 0.01384 0.00714 -0.0909 0.0217 1.0000
7.750 1.1988 0.01428 0.00755 -0.0889 0.0161 1.0000
8.000 1.2154 0.01471 0.00798 -0.0869 0.0135 1.0000
8.250 1.2324 0.01512 0.00841 -0.0851 0.0118 1.0000
8.500 1.2498 0.01552 0.00884 -0.0833 0.0108 1.0000
8.750 1.2661 0.01599 0.00932 -0.0815 0.0098 1.0000
9.000 1.2813 0.01652 0.00989 -0.0795 0.0088 1.0000
9.250 1.2974 0.01701 0.01042 -0.0776 0.0083 1.0000
9.500 1.3134 0.01751 0.01096 -0.0758 0.0079 1.0000
9.750 1.3288 0.01805 0.01154 -0.0740 0.0075 1.0000
10.000 1.3436 0.01863 0.01215 -0.0722 0.0070 1.0000
10.250 1.3576 0.01928 0.01283 -0.0702 0.0067 1.0000
10.500 1.3700 0.02003 0.01362 -0.0681 0.0061 1.0000
10.750 1.3832 0.02075 0.01441 -0.0662 0.0059 1.0000
11.000 1.3969 0.02145 0.01516 -0.0645 0.0056 1.0000
11.250 1.4095 0.02224 0.01601 -0.0627 0.0054 1.0000
11.500 1.4217 0.02308 0.01690 -0.0608 0.0053 1.0000
11.750 1.4334 0.02396 0.01784 -0.0591 0.0051 1.0000
12.000 1.4444 0.02492 0.01887 -0.0573 0.0049 1.0000
12.250 1.4556 0.02589 0.01989 -0.0556 0.0047 1.0000
12.500 1.4651 0.02701 0.02107 -0.0538 0.0045 1.0000
12.750 1.4735 0.02825 0.02237 -0.0521 0.0044 1.0000
13.000 1.4801 0.02968 0.02389 -0.0502 0.0042 1.0000
13.250 1.4852 0.03127 0.02557 -0.0484 0.0041 1.0000
13.500 1.4935 0.03262 0.02700 -0.0470 0.0040 1.0000
13.750 1.5012 0.03407 0.02853 -0.0456 0.0039 1.0000
14.000 1.5069 0.03572 0.03026 -0.0442 0.0039 1.0000
14.250 1.5122 0.03746 0.03209 -0.0429 0.0038 1.0000
14.500 1.5177 0.03924 0.03396 -0.0418 0.0037 1.0000
14.750 1.5218 0.04120 0.03601 -0.0407 0.0036 1.0000
15.000 1.5240 0.04342 0.03834 -0.0397 0.0036 1.0000
15.250 1.5287 0.04545 0.04044 -0.0390 0.0034 1.0000
15.500 1.5311 0.04780 0.04289 -0.0383 0.0034 1.0000
15.750 1.5312 0.05050 0.04571 -0.0377 0.0033 1.0000
16.000 1.5357 0.05275 0.04803 -0.0374 0.0032 1.0000
16.250 1.5344 0.05580 0.05118 -0.0372 0.0032 1.0000
16.500 1.5316 0.05915 0.05465 -0.0372 0.0031 1.0000
16.750 1.5321 0.06216 0.05774 -0.0374 0.0031 1.0000
17.000 1.5295 0.06567 0.06135 -0.0378 0.0030 1.0000
17.250 1.5235 0.06981 0.06561 -0.0384 0.0029 1.0000
17.500 1.5171 0.07415 0.07007 -0.0394 0.0029 1.0000
17.750 1.5094 0.07883 0.07487 -0.0407 0.0029 1.0000
18.000 1.4989 0.08411 0.08028 -0.0423 0.0029 1.0000
18.250 1.4883 0.08963 0.08593 -0.0443 0.0028 1.0000
18.500 1.4758 0.09566 0.09209 -0.0467 0.0028 1.0000
18.750 1.4586 0.10276 0.09935 -0.0499 0.0027 1.0000
19.000 1.4432 0.10975 0.10648 -0.0532 0.0027 1.0000
19.250 1.4286 0.11684 0.11370 -0.0568 0.0027 1.0000
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Polar data table (+)
Polar graphs
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