RAF 32 AIRFOIL (raf32-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 32 AIRFOIL (raf32-il) Reynolds number: 200,000 Max Cl/Cd: 84.76 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf32-il-200000-n5.txt Download as CSV file: xf-raf32-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 32 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5613 0.04395 0.03984 -0.1155 0.9638 0.0212
-11.000 -0.5650 0.03657 0.03203 -0.1267 0.9521 0.0215
-10.750 -0.5529 0.03310 0.02823 -0.1305 0.9451 0.0222
-10.500 -0.5384 0.03045 0.02522 -0.1323 0.9385 0.0232
-10.250 -0.5178 0.02831 0.02281 -0.1341 0.9334 0.0244
-10.000 -0.4882 0.02708 0.02147 -0.1364 0.9308 0.0258
-9.750 -0.4702 0.02603 0.02027 -0.1360 0.9240 0.0271
-9.500 -0.4452 0.02462 0.01861 -0.1369 0.9198 0.0289
-9.250 -0.4164 0.02340 0.01720 -0.1384 0.9171 0.0309
-9.000 -0.3941 0.02298 0.01672 -0.1380 0.9113 0.0329
-8.750 -0.3684 0.02221 0.01578 -0.1383 0.9067 0.0356
-8.500 -0.3390 0.02129 0.01466 -0.1394 0.9036 0.0385
-8.250 -0.3072 0.02088 0.01417 -0.1407 0.9009 0.0415
-8.000 -0.2872 0.02043 0.01357 -0.1395 0.8939 0.0448
-7.750 -0.2588 0.01976 0.01270 -0.1400 0.8900 0.0482
-7.500 -0.2278 0.01928 0.01216 -0.1411 0.8871 0.0514
-7.250 -0.2024 0.01888 0.01163 -0.1409 0.8820 0.0550
-7.000 -0.1764 0.01853 0.01105 -0.1407 0.8766 0.0580
-6.750 -0.1480 0.01783 0.01036 -0.1413 0.8727 0.0614
-6.500 -0.1162 0.01738 0.00980 -0.1423 0.8698 0.0650
-6.250 -0.0937 0.01707 0.00938 -0.1414 0.8635 0.0680
-6.000 -0.0665 0.01661 0.00881 -0.1414 0.8586 0.0706
-5.750 -0.0368 0.01603 0.00820 -0.1421 0.8548 0.0739
-5.500 -0.0105 0.01567 0.00778 -0.1419 0.8498 0.0766
-5.250 0.0148 0.01535 0.00739 -0.1415 0.8441 0.0794
-5.000 0.0439 0.01502 0.00695 -0.1418 0.8399 0.0821
-4.750 0.0734 0.01458 0.00646 -0.1423 0.8360 0.0848
-4.500 0.0963 0.01429 0.00617 -0.1414 0.8294 0.0879
-4.250 0.1243 0.01401 0.00582 -0.1415 0.8243 0.0917
-4.000 0.1552 0.01374 0.00545 -0.1421 0.8206 0.0966
-3.750 0.1783 0.01350 0.00525 -0.1413 0.8142 0.1044
-3.500 0.2054 0.01325 0.00500 -0.1412 0.8088 0.1156
-3.250 0.2352 0.01293 0.00472 -0.1417 0.8047 0.1385
-3.000 0.2589 0.01271 0.00462 -0.1410 0.7981 0.1742
-2.750 0.2858 0.01252 0.00451 -0.1409 0.7926 0.2112
-2.500 0.3157 0.01237 0.00437 -0.1413 0.7884 0.2417
-2.250 0.3396 0.01230 0.00436 -0.1406 0.7816 0.2638
-2.000 0.3669 0.01221 0.00427 -0.1404 0.7760 0.2863
-1.750 0.3958 0.01213 0.00418 -0.1406 0.7713 0.3088
-1.500 0.4199 0.01206 0.00419 -0.1399 0.7644 0.3305
-1.250 0.4474 0.01195 0.00413 -0.1399 0.7588 0.3617
-1.000 0.4730 0.01184 0.00415 -0.1394 0.7527 0.3989
-0.750 0.4982 0.01174 0.00416 -0.1389 0.7458 0.4366
-0.500 0.5260 0.01163 0.00412 -0.1388 0.7403 0.4754
-0.250 0.5494 0.01160 0.00419 -0.1379 0.7328 0.5110
0.000 0.5764 0.01154 0.00419 -0.1376 0.7271 0.5471
0.250 0.6013 0.01151 0.00424 -0.1370 0.7209 0.5818
0.500 0.6263 0.01148 0.00429 -0.1363 0.7146 0.6161
1.000 0.6765 0.01140 0.00441 -0.1350 0.7028 0.6903
1.250 0.7018 0.01133 0.00445 -0.1343 0.6971 0.7362
1.500 0.7280 0.01124 0.00449 -0.1338 0.6917 0.7963
1.750 0.7771 0.01107 0.00457 -0.1382 0.6855 1.0000
2.000 0.8041 0.01118 0.00461 -0.1380 0.6800 1.0000
2.250 0.8295 0.01131 0.00471 -0.1376 0.6740 1.0000
2.500 0.8547 0.01145 0.00482 -0.1371 0.6677 1.0000
2.750 0.8822 0.01157 0.00489 -0.1370 0.6625 1.0000
3.000 0.9060 0.01173 0.00506 -0.1363 0.6559 1.0000
3.250 0.9316 0.01188 0.00519 -0.1358 0.6498 1.0000
3.500 0.9574 0.01203 0.00532 -0.1354 0.6435 1.0000
3.750 0.9809 0.01219 0.00549 -0.1346 0.6354 1.0000
4.000 1.0056 0.01234 0.00561 -0.1339 0.6271 1.0000
4.250 1.0285 0.01250 0.00578 -0.1330 0.6175 1.0000
4.500 1.0514 0.01267 0.00596 -0.1320 0.6082 1.0000
5.000 1.0951 0.01303 0.00632 -0.1296 0.5865 1.0000
5.250 1.1160 0.01322 0.00652 -0.1282 0.5751 1.0000
5.500 1.1363 0.01342 0.00672 -0.1267 0.5626 1.0000
5.750 1.1561 0.01364 0.00694 -0.1251 0.5503 1.0000
6.000 1.1749 0.01387 0.00720 -0.1234 0.5374 1.0000
6.250 1.1928 0.01411 0.00746 -0.1215 0.5234 1.0000
6.500 1.2091 0.01438 0.00773 -0.1193 0.5081 1.0000
6.750 1.2234 0.01467 0.00802 -0.1167 0.4917 1.0000
7.250 1.2449 0.01552 0.00872 -0.1103 0.4482 1.0000
7.500 1.2536 0.01607 0.00920 -0.1070 0.4247 1.0000
7.750 1.2635 0.01665 0.00972 -0.1039 0.4025 1.0000
8.000 1.2701 0.01738 0.01035 -0.1005 0.3762 1.0000
8.250 1.2734 0.01828 0.01111 -0.0966 0.3418 1.0000
8.500 1.2724 0.01944 0.01207 -0.0924 0.3008 1.0000
8.750 1.2693 0.02084 0.01323 -0.0881 0.2616 1.0000
9.000 1.2680 0.02230 0.01451 -0.0844 0.2283 1.0000
9.250 1.2705 0.02367 0.01576 -0.0813 0.2030 1.0000
9.500 1.2738 0.02507 0.01706 -0.0786 0.1764 1.0000
9.750 1.2759 0.02662 0.01847 -0.0759 0.1462 1.0000
10.000 1.2767 0.02834 0.02003 -0.0732 0.1172 1.0000
10.250 1.2781 0.03010 0.02166 -0.0707 0.0963 1.0000
10.500 1.2824 0.03172 0.02325 -0.0687 0.0841 1.0000
10.750 1.2874 0.03333 0.02485 -0.0668 0.0748 1.0000
11.000 1.2939 0.03487 0.02643 -0.0651 0.0675 1.0000
11.250 1.2995 0.03653 0.02812 -0.0635 0.0610 1.0000
11.500 1.3053 0.03823 0.02985 -0.0620 0.0547 1.0000
11.750 1.3120 0.03989 0.03159 -0.0606 0.0488 1.0000
12.000 1.3170 0.04175 0.03347 -0.0593 0.0433 1.0000
12.250 1.3227 0.04359 0.03541 -0.0580 0.0386 1.0000
12.500 1.3272 0.04560 0.03744 -0.0568 0.0347 1.0000
12.750 1.3300 0.04783 0.03972 -0.0557 0.0318 1.0000
13.000 1.3346 0.04995 0.04194 -0.0547 0.0295 1.0000
13.250 1.3373 0.05231 0.04437 -0.0538 0.0276 1.0000
13.500 1.3383 0.05491 0.04703 -0.0530 0.0261 1.0000
13.750 1.3394 0.05760 0.04980 -0.0522 0.0247 1.0000
14.000 1.3420 0.06016 0.05248 -0.0516 0.0235 1.0000
14.250 1.3440 0.06283 0.05526 -0.0512 0.0224 1.0000
14.500 1.3452 0.06566 0.05820 -0.0508 0.0216 1.0000
14.750 1.3440 0.06886 0.06146 -0.0505 0.0207 1.0000
15.000 1.3422 0.07219 0.06487 -0.0504 0.0201 1.0000
15.250 1.3445 0.07507 0.06790 -0.0503 0.0192 1.0000
15.500 1.3452 0.07818 0.07113 -0.0503 0.0186 1.0000
15.750 1.3455 0.08141 0.07447 -0.0505 0.0180 1.0000
16.000 1.3454 0.08475 0.07792 -0.0507 0.0174 1.0000
16.250 1.3449 0.08819 0.08145 -0.0512 0.0170 1.0000
16.500 1.3433 0.09183 0.08518 -0.0517 0.0166 1.0000
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