DAE-31 AIRFOIL (dae31-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DAE-31 AIRFOIL (dae31-il) Reynolds number: 500,000 Max Cl/Cd: 139.39 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dae31-il-500000.txt Download as CSV file: xf-dae31-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: DAE-31 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.0032 0.10014 0.09705 -0.0983 0.8514 0.0189
-9.750 0.0057 0.09739 0.09430 -0.1003 0.8481 0.0195
-9.500 0.0059 0.09488 0.09178 -0.1024 0.8448 0.0196
-9.250 0.0171 0.09187 0.08876 -0.1028 0.8424 0.0197
-9.000 0.0291 0.08944 0.08633 -0.1032 0.8400 0.0198
-8.750 0.0391 0.08717 0.08407 -0.1037 0.8374 0.0200
-8.500 0.0480 0.08494 0.08186 -0.1045 0.8343 0.0203
-8.250 0.0560 0.08266 0.07958 -0.1053 0.8313 0.0205
-8.000 0.0639 0.08039 0.07731 -0.1061 0.8284 0.0208
-7.750 0.0710 0.07806 0.07497 -0.1069 0.8254 0.0214
-7.500 0.0727 0.07536 0.07227 -0.1084 0.8219 0.0225
-7.250 0.0662 0.07238 0.06935 -0.1105 0.8177 0.0227
-7.000 0.0684 0.06981 0.06681 -0.1108 0.8140 0.0228
-6.750 0.0812 0.06800 0.06500 -0.1102 0.8113 0.0231
-6.500 0.0908 0.06612 0.06311 -0.1105 0.8084 0.0234
-6.250 0.1008 0.06401 0.06097 -0.1118 0.8055 0.0238
-6.000 0.1111 0.06163 0.05862 -0.1138 0.8023 0.0245
-5.750 0.1242 0.05467 0.05164 -0.1266 0.7974 0.0262
-5.500 0.1375 0.05305 0.05002 -0.1258 0.7944 0.0264
-5.250 0.1545 0.05128 0.04823 -0.1265 0.7915 0.0267
-5.000 0.1741 0.04892 0.04583 -0.1290 0.7887 0.0273
-4.500 0.2267 0.03964 0.03634 -0.1417 0.7823 0.0304
-4.250 0.2503 0.03756 0.03423 -0.1435 0.7791 0.0310
-4.000 0.2855 0.03022 0.02645 -0.1509 0.7758 0.0342
-3.750 0.3100 0.02898 0.02517 -0.1516 0.7730 0.0348
-3.500 0.3373 0.02704 0.02307 -0.1529 0.7705 0.0363
-3.250 0.3669 0.02375 0.01940 -0.1548 0.7678 0.0395
-3.000 0.3991 0.01607 0.01051 -0.1563 0.7649 0.0273
-2.750 0.4273 0.01492 0.00913 -0.1564 0.7616 0.0277
-2.500 0.4558 0.01395 0.00795 -0.1564 0.7583 0.0281
-2.250 0.4845 0.01303 0.00683 -0.1564 0.7553 0.0282
-2.000 0.5132 0.01237 0.00602 -0.1563 0.7525 0.0289
-1.750 0.5417 0.01196 0.00547 -0.1562 0.7493 0.0298
-1.500 0.5692 0.01142 0.00499 -0.1562 0.7454 0.0310
-1.250 0.5975 0.01109 0.00464 -0.1562 0.7415 0.0328
-1.000 0.6259 0.01075 0.00430 -0.1562 0.7379 0.0354
-0.750 0.6547 0.01050 0.00399 -0.1562 0.7346 0.0385
-0.500 0.6828 0.01028 0.00379 -0.1562 0.7307 0.0426
-0.250 0.7108 0.01003 0.00358 -0.1561 0.7261 0.0497
0.000 0.7393 0.00977 0.00337 -0.1561 0.7218 0.0680
0.250 0.7677 0.00942 0.00323 -0.1563 0.7179 0.1402
0.500 0.7953 0.00913 0.00325 -0.1564 0.7133 0.2566
0.750 0.8224 0.00882 0.00329 -0.1564 0.7080 0.3949
1.000 0.8489 0.00842 0.00332 -0.1562 0.7031 0.5757
1.250 0.8779 0.00762 0.00329 -0.1561 0.6983 1.0000
1.500 0.9053 0.00766 0.00329 -0.1560 0.6919 1.0000
1.750 0.9332 0.00768 0.00323 -0.1559 0.6860 1.0000
2.000 0.9609 0.00774 0.00322 -0.1558 0.6799 1.0000
2.250 0.9882 0.00779 0.00324 -0.1556 0.6726 1.0000
2.500 1.0159 0.00787 0.00320 -0.1555 0.6662 1.0000
2.750 1.0427 0.00793 0.00327 -0.1553 0.6582 1.0000
3.000 1.0698 0.00802 0.00327 -0.1550 0.6506 1.0000
3.250 1.0964 0.00810 0.00335 -0.1548 0.6416 1.0000
3.750 1.1489 0.00833 0.00348 -0.1541 0.6224 1.0000
4.000 1.1747 0.00847 0.00356 -0.1537 0.6124 1.0000
4.250 1.2001 0.00863 0.00367 -0.1533 0.6013 1.0000
4.500 1.2252 0.00879 0.00380 -0.1528 0.5896 1.0000
4.750 1.2498 0.00899 0.00395 -0.1522 0.5779 1.0000
5.000 1.2737 0.00922 0.00411 -0.1515 0.5656 1.0000
5.250 1.2975 0.00943 0.00430 -0.1508 0.5524 1.0000
5.500 1.3208 0.00968 0.00450 -0.1501 0.5394 1.0000
5.750 1.3432 0.00995 0.00472 -0.1492 0.5262 1.0000
6.000 1.3647 0.01026 0.00498 -0.1481 0.5124 1.0000
6.250 1.3853 0.01059 0.00525 -0.1469 0.4982 1.0000
6.500 1.4057 0.01092 0.00553 -0.1457 0.4836 1.0000
6.750 1.4251 0.01126 0.00583 -0.1443 0.4692 1.0000
7.000 1.4432 0.01164 0.00617 -0.1427 0.4549 1.0000
7.250 1.4600 0.01204 0.00653 -0.1409 0.4411 1.0000
7.500 1.4729 0.01248 0.00691 -0.1383 0.4269 1.0000
7.750 1.4839 0.01296 0.00735 -0.1355 0.4128 1.0000
8.000 1.4960 0.01346 0.00782 -0.1330 0.3985 1.0000
8.250 1.5075 0.01403 0.00837 -0.1305 0.3843 1.0000
8.500 1.5185 0.01467 0.00897 -0.1280 0.3703 1.0000
8.750 1.5291 0.01539 0.00963 -0.1257 0.3561 1.0000
9.000 1.5393 0.01616 0.01036 -0.1233 0.3419 1.0000
9.250 1.5490 0.01702 0.01117 -0.1210 0.3271 1.0000
9.500 1.5590 0.01789 0.01200 -0.1188 0.3124 1.0000
9.750 1.5695 0.01879 0.01287 -0.1168 0.2980 1.0000
10.000 1.5798 0.01972 0.01377 -0.1148 0.2840 1.0000
10.250 1.5892 0.02075 0.01476 -0.1128 0.2700 1.0000
10.500 1.5985 0.02180 0.01577 -0.1108 0.2567 1.0000
10.750 1.6066 0.02296 0.01689 -0.1088 0.2435 1.0000
11.000 1.6144 0.02418 0.01807 -0.1068 0.2300 1.0000
11.250 1.6218 0.02546 0.01930 -0.1049 0.2170 1.0000
11.500 1.6308 0.02666 0.02049 -0.1032 0.2046 1.0000
11.750 1.6391 0.02794 0.02175 -0.1015 0.1936 1.0000
12.000 1.6463 0.02933 0.02312 -0.0998 0.1830 1.0000
12.500 1.6606 0.03223 0.02599 -0.0965 0.1631 1.0000
12.750 1.6674 0.03377 0.02753 -0.0950 0.1540 1.0000
13.000 1.6725 0.03550 0.02924 -0.0935 0.1447 1.0000
13.250 1.6792 0.03715 0.03089 -0.0921 0.1359 1.0000
13.500 1.6857 0.03885 0.03261 -0.0909 0.1278 1.0000
13.750 1.6899 0.04081 0.03456 -0.0895 0.1195 1.0000
14.000 1.6948 0.04277 0.03652 -0.0884 0.1117 1.0000
14.250 1.7006 0.04468 0.03846 -0.0873 0.1048 1.0000
14.500 1.7036 0.04692 0.04071 -0.0862 0.0986 1.0000
14.750 1.7087 0.04900 0.04282 -0.0853 0.0925 1.0000
15.000 1.7121 0.05131 0.04517 -0.0845 0.0869 1.0000
15.250 1.7137 0.05389 0.04776 -0.0837 0.0814 1.0000
15.500 1.7177 0.05623 0.05016 -0.0830 0.0760 1.0000
15.750 1.7185 0.05901 0.05297 -0.0824 0.0709 1.0000
16.000 1.7186 0.06193 0.05592 -0.0819 0.0658 1.0000
16.250 1.7200 0.06476 0.05881 -0.0815 0.0610 1.0000
16.500 1.7188 0.06800 0.06209 -0.0813 0.0565 1.0000
16.750 1.7161 0.07148 0.06562 -0.0812 0.0524 1.0000
17.000 1.7150 0.07485 0.06905 -0.0812 0.0483 1.0000
17.250 1.7120 0.07854 0.07280 -0.0813 0.0448 1.0000
17.500 1.7068 0.08264 0.07695 -0.0816 0.0416 1.0000
17.750 1.7035 0.08652 0.08092 -0.0821 0.0386 1.0000
18.000 1.6968 0.09099 0.08546 -0.0828 0.0361 1.0000
18.250 1.6918 0.09528 0.08983 -0.0836 0.0336 1.0000
18.500 1.6847 0.09999 0.09463 -0.0846 0.0316 1.0000
18.750 1.6782 0.10466 0.09938 -0.0858 0.0295 1.0000
19.000 1.6696 0.10973 0.10454 -0.0872 0.0278 1.0000
19.250 1.6627 0.11460 0.10950 -0.0887 0.0261 1.0000
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