RAF 32 AIRFOIL (raf32-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 32 AIRFOIL (raf32-il) Reynolds number: 500,000 Max Cl/Cd: 116.56 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf32-il-500000-n5.txt Download as CSV file: xf-raf32-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.3973 0.14415 0.14168 -0.0470 0.9998 0.0101
-14.750 -0.3882 0.14020 0.13774 -0.0500 0.9990 0.0103
-14.500 -0.5188 0.10459 0.10195 -0.0654 0.9982 0.0119
-14.250 -0.5539 0.09216 0.08940 -0.0736 0.9966 0.0119
-14.000 -0.5858 0.08082 0.07793 -0.0819 0.9944 0.0118
-13.750 -0.6225 0.06934 0.06632 -0.0908 0.9909 0.0117
-13.500 -0.6596 0.05723 0.05405 -0.1021 0.9865 0.0115
-13.250 -0.6909 0.04604 0.04267 -0.1135 0.9790 0.0113
-13.000 -0.7083 0.03525 0.03161 -0.1275 0.9701 0.0112
-12.750 -0.7022 0.02878 0.02482 -0.1389 0.9613 0.0114
-12.500 -0.6809 0.02650 0.02234 -0.1426 0.9570 0.0119
-12.250 -0.6598 0.02465 0.02029 -0.1449 0.9523 0.0122
-12.000 -0.6390 0.02323 0.01871 -0.1461 0.9465 0.0126
-11.750 -0.6144 0.02168 0.01702 -0.1481 0.9418 0.0131
-11.500 -0.5935 0.02058 0.01579 -0.1484 0.9340 0.0135
-11.250 -0.5675 0.01958 0.01467 -0.1494 0.9283 0.0141
-11.000 -0.5452 0.01875 0.01371 -0.1494 0.9211 0.0147
-10.750 -0.5185 0.01796 0.01277 -0.1502 0.9164 0.0153
-10.500 -0.4976 0.01718 0.01188 -0.1497 0.9093 0.0161
-10.250 -0.4726 0.01648 0.01108 -0.1499 0.9037 0.0171
-10.000 -0.4482 0.01589 0.01039 -0.1499 0.8980 0.0182
-9.750 -0.4239 0.01536 0.00974 -0.1497 0.8916 0.0192
-9.500 -0.3983 0.01475 0.00904 -0.1498 0.8863 0.0206
-9.250 -0.3745 0.01426 0.00848 -0.1494 0.8804 0.0223
-9.000 -0.3493 0.01383 0.00796 -0.1492 0.8746 0.0242
-8.500 -0.2982 0.01306 0.00708 -0.1489 0.8636 0.0298
-8.250 -0.2721 0.01278 0.00678 -0.1487 0.8581 0.0335
-7.750 -0.2190 0.01235 0.00625 -0.1485 0.8483 0.0402
-7.500 -0.1923 0.01219 0.00603 -0.1484 0.8428 0.0433
-7.250 -0.1648 0.01205 0.00580 -0.1483 0.8379 0.0460
-7.000 -0.1382 0.01192 0.00559 -0.1481 0.8328 0.0475
-6.750 -0.1126 0.01162 0.00527 -0.1479 0.8274 0.0503
-6.500 -0.0857 0.01144 0.00504 -0.1478 0.8227 0.0526
-6.250 -0.0588 0.01129 0.00482 -0.1476 0.8181 0.0548
-6.000 -0.0324 0.01115 0.00462 -0.1474 0.8129 0.0567
-5.750 -0.0053 0.01104 0.00443 -0.1473 0.8076 0.0580
-5.500 0.0207 0.01074 0.00409 -0.1470 0.8027 0.0606
-5.250 0.0468 0.01053 0.00386 -0.1467 0.7974 0.0627
-5.000 0.0734 0.01036 0.00364 -0.1465 0.7923 0.0645
-4.750 0.1004 0.01022 0.00344 -0.1464 0.7877 0.0663
-4.500 0.1268 0.01008 0.00325 -0.1461 0.7822 0.0679
-4.250 0.1535 0.00995 0.00307 -0.1459 0.7765 0.0692
-4.000 0.1803 0.00981 0.00287 -0.1457 0.7713 0.0713
-3.750 0.2066 0.00965 0.00271 -0.1454 0.7657 0.0748
-3.500 0.2333 0.00953 0.00256 -0.1451 0.7599 0.0784
-3.250 0.2601 0.00944 0.00243 -0.1449 0.7545 0.0827
-3.000 0.2864 0.00929 0.00231 -0.1446 0.7481 0.0935
-2.750 0.3126 0.00915 0.00219 -0.1444 0.7421 0.1125
-2.500 0.3386 0.00895 0.00210 -0.1441 0.7359 0.1461
-2.250 0.3644 0.00880 0.00204 -0.1437 0.7289 0.1800
-2.000 0.3905 0.00871 0.00199 -0.1434 0.7218 0.2085
-1.750 0.4164 0.00864 0.00195 -0.1430 0.7133 0.2296
-1.500 0.4425 0.00860 0.00192 -0.1426 0.7058 0.2486
-1.250 0.4686 0.00857 0.00190 -0.1423 0.6984 0.2658
-1.000 0.4949 0.00856 0.00189 -0.1420 0.6920 0.2812
-0.750 0.5211 0.00852 0.00190 -0.1416 0.6852 0.3018
-0.250 0.5731 0.00845 0.00193 -0.1409 0.6729 0.3534
0.000 0.5988 0.00842 0.00196 -0.1405 0.6665 0.3822
0.250 0.6244 0.00838 0.00200 -0.1401 0.6609 0.4193
0.500 0.6502 0.00832 0.00206 -0.1397 0.6552 0.4608
0.750 0.6757 0.00831 0.00213 -0.1393 0.6496 0.4987
1.000 0.7013 0.00832 0.00220 -0.1388 0.6442 0.5306
1.250 0.7270 0.00832 0.00228 -0.1384 0.6384 0.5616
1.500 0.7524 0.00834 0.00236 -0.1379 0.6333 0.5899
1.750 0.7779 0.00837 0.00244 -0.1374 0.6284 0.6166
2.250 0.8276 0.00839 0.00263 -0.1362 0.6169 0.6779
2.500 0.8514 0.00839 0.00274 -0.1353 0.6107 0.7173
2.750 0.8741 0.00836 0.00285 -0.1342 0.6031 0.7658
3.000 0.8958 0.00818 0.00297 -0.1327 0.5961 0.8765
3.250 0.9436 0.00827 0.00310 -0.1373 0.5850 1.0000
3.500 0.9669 0.00840 0.00321 -0.1364 0.5751 1.0000
3.750 0.9892 0.00857 0.00333 -0.1352 0.5641 1.0000
4.000 1.0113 0.00872 0.00345 -0.1341 0.5518 1.0000
4.250 1.0336 0.00887 0.00358 -0.1330 0.5399 1.0000
4.500 1.0549 0.00905 0.00373 -0.1317 0.5271 1.0000
4.750 1.0755 0.00925 0.00389 -0.1303 0.5141 1.0000
5.000 1.0953 0.00946 0.00407 -0.1287 0.5001 1.0000
5.250 1.1129 0.00969 0.00425 -0.1267 0.4847 1.0000
5.500 1.1287 0.00998 0.00447 -0.1243 0.4664 1.0000
5.750 1.1442 0.01030 0.00473 -0.1219 0.4481 1.0000
6.000 1.1586 0.01067 0.00502 -0.1194 0.4279 1.0000
6.250 1.1720 0.01110 0.00536 -0.1167 0.4069 1.0000
6.500 1.1870 0.01151 0.00571 -0.1144 0.3864 1.0000
6.750 1.2009 0.01198 0.00609 -0.1120 0.3638 1.0000
7.000 1.2085 0.01270 0.00662 -0.1085 0.3261 1.0000
7.250 1.2105 0.01371 0.00735 -0.1042 0.2746 1.0000
7.500 1.2145 0.01472 0.00812 -0.1005 0.2348 1.0000
7.750 1.2222 0.01560 0.00886 -0.0975 0.2062 1.0000
8.000 1.2321 0.01640 0.00955 -0.0948 0.1807 1.0000
8.250 1.2406 0.01732 0.01033 -0.0921 0.1532 1.0000
8.500 1.2462 0.01842 0.01125 -0.0891 0.1203 1.0000
8.750 1.2521 0.01955 0.01224 -0.0863 0.0945 1.0000
9.000 1.2615 0.02053 0.01316 -0.0840 0.0802 1.0000
9.250 1.2721 0.02146 0.01406 -0.0819 0.0706 1.0000
9.500 1.2835 0.02237 0.01496 -0.0800 0.0643 1.0000
9.750 1.2962 0.02321 0.01583 -0.0784 0.0589 1.0000
10.000 1.3070 0.02422 0.01682 -0.0765 0.0534 1.0000
10.250 1.3200 0.02509 0.01774 -0.0750 0.0483 1.0000
10.500 1.3302 0.02617 0.01881 -0.0733 0.0416 1.0000
10.750 1.3400 0.02731 0.01994 -0.0716 0.0347 1.0000
11.000 1.3491 0.02853 0.02116 -0.0699 0.0294 1.0000
11.250 1.3574 0.02984 0.02247 -0.0682 0.0257 1.0000
11.500 1.3669 0.03109 0.02376 -0.0667 0.0233 1.0000
11.750 1.3749 0.03250 0.02521 -0.0652 0.0212 1.0000
12.000 1.3832 0.03391 0.02666 -0.0637 0.0195 1.0000
12.250 1.3916 0.03535 0.02816 -0.0624 0.0182 1.0000
12.500 1.3989 0.03692 0.02978 -0.0610 0.0170 1.0000
12.750 1.4055 0.03860 0.03151 -0.0597 0.0161 1.0000
13.000 1.4133 0.04021 0.03319 -0.0586 0.0153 1.0000
13.250 1.4201 0.04195 0.03500 -0.0575 0.0146 1.0000
13.500 1.4266 0.04375 0.03687 -0.0565 0.0139 1.0000
13.750 1.4306 0.04585 0.03902 -0.0554 0.0132 1.0000
14.000 1.4364 0.04782 0.04106 -0.0545 0.0127 1.0000
14.250 1.4418 0.04987 0.04320 -0.0537 0.0122 1.0000
14.500 1.4464 0.05204 0.04546 -0.0530 0.0118 1.0000
14.750 1.4500 0.05438 0.04787 -0.0523 0.0113 1.0000
15.000 1.4529 0.05683 0.05039 -0.0517 0.0110 1.0000
15.250 1.4539 0.05957 0.05320 -0.0512 0.0106 1.0000
15.500 1.4553 0.06233 0.05605 -0.0508 0.0104 1.0000
15.750 1.4579 0.06498 0.05880 -0.0506 0.0101 1.0000
16.000 1.4592 0.06783 0.06176 -0.0504 0.0098 1.0000
16.250 1.4601 0.07080 0.06483 -0.0503 0.0095 1.0000
16.500 1.4608 0.07386 0.06798 -0.0504 0.0092 1.0000
16.750 1.4603 0.07714 0.07135 -0.0505 0.0090 1.0000
17.000 1.4597 0.08048 0.07479 -0.0508 0.0088 1.0000
17.250 1.4577 0.08407 0.07846 -0.0513 0.0086 1.0000
17.500 1.4529 0.08817 0.08265 -0.0520 0.0084 1.0000
17.750 1.4498 0.09209 0.08668 -0.0528 0.0082 1.0000
18.000 1.4473 0.09600 0.09070 -0.0536 0.0081 1.0000
18.250 1.4438 0.10009 0.09491 -0.0547 0.0080 1.0000
18.500 1.4396 0.10437 0.09930 -0.0559 0.0078 1.0000
18.750 1.4357 0.10867 0.10371 -0.0572 0.0077 1.0000
19.000 1.4313 0.11310 0.10826 -0.0588 0.0075 1.0000
19.250 1.4267 0.11762 0.11288 -0.0605 0.0074 1.0000
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Polar data table (+)
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