DFVLR R-4 AIRFOIL (dfvlrr4-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DFVLR R-4 AIRFOIL (dfvlrr4-il) Reynolds number: 500,000 Max Cl/Cd: 72.88 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dfvlrr4-il-500000.txt Download as CSV file: xf-dfvlrr4-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: DFVLR R-4 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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.7944 0.08611 0.08301 -0.0594 1.0000 0.0181
-15.000 -0.8262 0.07654 0.07327 -0.0651 1.0000 0.0179
-14.750 -0.8521 0.06887 0.06540 -0.0696 1.0000 0.0179
-14.500 -0.8736 0.06271 0.05905 -0.0727 1.0000 0.0179
-14.250 -0.8912 0.05772 0.05388 -0.0747 1.0000 0.0179
-14.000 -0.9074 0.05331 0.04928 -0.0758 1.0000 0.0179
-13.750 -0.9193 0.04994 0.04573 -0.0761 1.0000 0.0180
-13.500 -0.9301 0.04706 0.04268 -0.0756 1.0000 0.0181
-13.250 -0.9432 0.04414 0.03959 -0.0743 1.0000 0.0182
-13.000 -0.9552 0.04138 0.03666 -0.0723 1.0000 0.0182
-12.750 -0.9688 0.03868 0.03378 -0.0694 1.0000 0.0183
-12.500 -0.9799 0.03666 0.03165 -0.0658 1.0000 0.0186
-12.250 -0.9926 0.03539 0.03031 -0.0611 1.0000 0.0187
-12.000 -1.0124 0.03450 0.02935 -0.0550 1.0000 0.0187
-11.750 -1.0208 0.03358 0.02840 -0.0509 1.0000 0.0189
-11.500 -1.0003 0.03212 0.02687 -0.0523 0.9984 0.0193
-11.250 -0.9738 0.03065 0.02528 -0.0547 0.9963 0.0198
-11.000 -0.9461 0.02922 0.02374 -0.0569 0.9947 0.0203
-10.750 -0.9210 0.02777 0.02215 -0.0582 0.9925 0.0208
-10.500 -0.8945 0.02642 0.02065 -0.0594 0.9902 0.0212
-10.250 -0.8666 0.02516 0.01926 -0.0608 0.9884 0.0216
-10.000 -0.8372 0.02408 0.01806 -0.0622 0.9869 0.0220
-9.750 -0.8068 0.02310 0.01696 -0.0639 0.9857 0.0224
-9.500 -0.7801 0.02150 0.01532 -0.0649 0.9848 0.0232
-9.250 -0.7563 0.02063 0.01444 -0.0653 0.9809 0.0238
-9.000 -0.7267 0.01987 0.01365 -0.0667 0.9786 0.0246
-8.750 -0.6952 0.01917 0.01291 -0.0685 0.9768 0.0257
-8.500 -0.6624 0.01853 0.01220 -0.0704 0.9754 0.0268
-8.250 -0.6297 0.01754 0.01117 -0.0726 0.9743 0.0282
-8.000 -0.5952 0.01676 0.01040 -0.0751 0.9734 0.0298
-7.750 -0.5595 0.01617 0.00977 -0.0776 0.9727 0.0319
-7.500 -0.5354 0.01566 0.00921 -0.0775 0.9676 0.0337
-7.250 -0.5021 0.01491 0.00849 -0.0797 0.9657 0.0377
-7.000 -0.4671 0.01427 0.00786 -0.0820 0.9643 0.0436
-6.750 -0.4312 0.01370 0.00732 -0.0845 0.9633 0.0522
-6.500 -0.3947 0.01320 0.00687 -0.0870 0.9624 0.0623
-6.250 -0.3583 0.01276 0.00648 -0.0894 0.9615 0.0744
-6.000 -0.3218 0.01231 0.00608 -0.0919 0.9607 0.0896
-5.750 -0.2851 0.01180 0.00568 -0.0945 0.9599 0.1123
-5.500 -0.2473 0.01111 0.00523 -0.0975 0.9591 0.1634
-5.250 -0.2022 0.00941 0.00445 -0.1038 0.9589 0.3676
-5.000 -0.1699 0.00892 0.00424 -0.1055 0.9553 0.4475
-4.750 -0.1351 0.00861 0.00409 -0.1075 0.9529 0.4980
-4.500 -0.1008 0.00841 0.00400 -0.1091 0.9509 0.5354
-4.250 -0.0671 0.00830 0.00392 -0.1104 0.9491 0.5587
-4.000 -0.0334 0.00821 0.00387 -0.1117 0.9474 0.5785
-3.750 0.0002 0.00817 0.00385 -0.1130 0.9458 0.5982
-3.500 0.0337 0.00818 0.00387 -0.1141 0.9443 0.6192
-3.250 0.0610 0.00829 0.00400 -0.1140 0.9402 0.6344
-3.000 0.0897 0.00838 0.00412 -0.1140 0.9367 0.6451
-2.750 0.1204 0.00843 0.00416 -0.1146 0.9341 0.6537
-2.500 0.1512 0.00850 0.00424 -0.1151 0.9319 0.6612
-2.250 0.1827 0.00857 0.00429 -0.1158 0.9300 0.6689
-2.000 0.2110 0.00869 0.00444 -0.1157 0.9266 0.6743
-1.750 0.2397 0.00873 0.00445 -0.1158 0.9214 0.6807
-1.500 0.2695 0.00866 0.00438 -0.1159 0.9167 0.6845
-1.250 0.2977 0.00863 0.00435 -0.1155 0.9105 0.6879
-1.000 0.3253 0.00850 0.00418 -0.1149 0.9002 0.6923
-0.750 0.3533 0.00838 0.00399 -0.1144 0.8866 0.6978
-0.500 0.3795 0.00835 0.00397 -0.1136 0.8753 0.7007
-0.250 0.4072 0.00835 0.00395 -0.1131 0.8656 0.7040
0.000 0.4353 0.00836 0.00396 -0.1130 0.8555 0.7077
0.250 0.4657 0.00835 0.00391 -0.1134 0.8474 0.7120
0.500 0.4933 0.00836 0.00393 -0.1131 0.8364 0.7148
0.750 0.5202 0.00841 0.00400 -0.1127 0.8242 0.7173
1.000 0.5478 0.00846 0.00405 -0.1123 0.8106 0.7203
1.250 0.5758 0.00850 0.00407 -0.1122 0.7935 0.7235
1.500 0.6045 0.00856 0.00403 -0.1122 0.7701 0.7272
1.750 0.6311 0.00866 0.00404 -0.1117 0.7331 0.7297
2.000 0.6496 0.00922 0.00413 -0.1095 0.6216 0.7317
2.250 0.6629 0.01038 0.00458 -0.1066 0.4738 0.7341
2.500 0.6805 0.01136 0.00500 -0.1049 0.3555 0.7367
2.750 0.7007 0.01223 0.00538 -0.1037 0.2543 0.7398
3.000 0.7241 0.01291 0.00570 -0.1032 0.1874 0.7431
3.250 0.7483 0.01338 0.00597 -0.1027 0.1519 0.7454
3.500 0.7721 0.01378 0.00629 -0.1019 0.1327 0.7475
3.750 0.7968 0.01410 0.00659 -0.1012 0.1222 0.7499
4.000 0.8217 0.01444 0.00691 -0.1007 0.1145 0.7528
4.250 0.8475 0.01476 0.00720 -0.1004 0.1084 0.7557
4.500 0.8730 0.01518 0.00757 -0.1001 0.1021 0.7585
4.750 0.9000 0.01541 0.00782 -0.1001 0.0988 0.7607
5.000 0.9247 0.01568 0.00812 -0.0995 0.0953 0.7624
5.250 0.9483 0.01606 0.00851 -0.0987 0.0921 0.7642
5.500 0.9700 0.01666 0.00912 -0.0976 0.0886 0.7663
5.750 0.9950 0.01693 0.00945 -0.0971 0.0873 0.7687
6.000 1.0201 0.01725 0.00981 -0.0967 0.0856 0.7713
6.250 1.0454 0.01758 0.01017 -0.0963 0.0836 0.7737
6.500 1.0709 0.01795 0.01054 -0.0961 0.0816 0.7759
6.750 1.0942 0.01832 0.01094 -0.0954 0.0797 0.7775
7.000 1.1151 0.01895 0.01159 -0.0942 0.0774 0.7792
7.250 1.1365 0.01957 0.01226 -0.0931 0.0756 0.7810
7.500 1.1609 0.01979 0.01257 -0.0926 0.0742 0.7830
7.750 1.1851 0.02003 0.01287 -0.0920 0.0719 0.7850
8.000 1.2093 0.02026 0.01312 -0.0915 0.0693 0.7873
8.250 1.2319 0.02068 0.01351 -0.0908 0.0667 0.7896
8.500 1.2533 0.02132 0.01419 -0.0900 0.0643 0.7917
8.750 1.2763 0.02154 0.01450 -0.0892 0.0622 0.7934
9.000 1.2981 0.02177 0.01477 -0.0883 0.0598 0.7951
9.250 1.3179 0.02217 0.01516 -0.0870 0.0573 0.7969
9.500 1.3352 0.02278 0.01581 -0.0854 0.0549 0.7989
9.750 1.3545 0.02299 0.01611 -0.0840 0.0527 0.8010
10.000 1.3737 0.02330 0.01646 -0.0826 0.0505 0.8032
10.250 1.3920 0.02384 0.01700 -0.0813 0.0485 0.8052
10.500 1.4097 0.02452 0.01772 -0.0799 0.0467 0.8069
10.750 1.4299 0.02491 0.01821 -0.0789 0.0450 0.8085
11.000 1.4490 0.02533 0.01871 -0.0777 0.0431 0.8100
11.250 1.4671 0.02583 0.01924 -0.0764 0.0414 0.8118
11.500 1.4826 0.02656 0.02001 -0.0747 0.0397 0.8137
11.750 1.5001 0.02716 0.02072 -0.0734 0.0381 0.8157
12.000 1.5171 0.02779 0.02140 -0.0721 0.0364 0.8176
12.250 1.5316 0.02865 0.02225 -0.0706 0.0346 0.8195
12.500 1.5448 0.02963 0.02332 -0.0689 0.0330 0.8213
12.750 1.5598 0.03046 0.02427 -0.0675 0.0314 0.8229
13.000 1.5723 0.03142 0.02530 -0.0658 0.0299 0.8244
13.250 1.5798 0.03280 0.02673 -0.0636 0.0283 0.8260
13.500 1.5913 0.03389 0.02795 -0.0620 0.0271 0.8277
13.750 1.6013 0.03510 0.02927 -0.0603 0.0258 0.8296
14.000 1.6080 0.03662 0.03086 -0.0584 0.0246 0.8316
14.250 1.6074 0.03879 0.03309 -0.0560 0.0234 0.8337
14.500 1.6172 0.04016 0.03462 -0.0547 0.0224 0.8357
14.750 1.6238 0.04183 0.03642 -0.0532 0.0214 0.8374
15.000 1.6280 0.04370 0.03840 -0.0517 0.0205 0.8391
15.250 1.6285 0.04595 0.04075 -0.0501 0.0197 0.8407
15.500 1.6233 0.04884 0.04376 -0.0486 0.0191 0.8424
15.750 1.6240 0.05129 0.04637 -0.0475 0.0185 0.8444
16.000 1.6218 0.05414 0.04937 -0.0466 0.0180 0.8465
16.250 1.6179 0.05731 0.05267 -0.0460 0.0175 0.8486
16.500 1.6119 0.06097 0.05647 -0.0459 0.0171 0.8505
17.000 1.5898 0.07041 0.06620 -0.0474 0.0165 0.8537
17.250 1.5732 0.07649 0.07244 -0.0493 0.0163 0.8552
17.500 1.5518 0.08387 0.08000 -0.0525 0.0161 0.8566
17.750 1.5284 0.09213 0.08847 -0.0565 0.0161 0.8578
18.000 1.5003 0.10170 0.09825 -0.0617 0.0161 0.8589
18.250 1.4687 0.11229 0.10904 -0.0676 0.0161 0.8598
18.500 1.4341 0.12372 0.12068 -0.0741 0.0163 0.8605
18.750 1.3979 0.13559 0.13276 -0.0810 0.0164 0.8610
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