DFVLR R-4 AIRFOIL (dfvlrr4-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: DFVLR R-4 AIRFOIL (dfvlrr4-il) Reynolds number: 100,000 Max Cl/Cd: 33.83 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dfvlrr4-il-100000-n5.txt Download as CSV file: xf-dfvlrr4-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6430 0.09035 0.08454 -0.0581 1.0000 0.0325
-12.750 -0.6761 0.08100 0.07506 -0.0638 1.0000 0.0321
-12.500 -0.7058 0.07383 0.06774 -0.0675 1.0000 0.0319
-12.250 -0.7323 0.06818 0.06192 -0.0694 1.0000 0.0318
-12.000 -0.7567 0.06360 0.05718 -0.0698 1.0000 0.0317
-11.750 -0.7793 0.05986 0.05327 -0.0688 1.0000 0.0317
-11.500 -0.8008 0.05679 0.05004 -0.0667 1.0000 0.0317
-11.250 -0.8228 0.05436 0.04747 -0.0633 1.0000 0.0318
-11.000 -0.8436 0.05223 0.04520 -0.0594 1.0000 0.0318
-10.750 -0.8571 0.04972 0.04246 -0.0565 1.0000 0.0320
-10.500 -0.8653 0.04721 0.03968 -0.0538 1.0000 0.0322
-10.250 -0.8681 0.04476 0.03691 -0.0514 1.0000 0.0326
-10.000 -0.8661 0.04241 0.03421 -0.0492 1.0000 0.0330
-9.750 -0.8588 0.04047 0.03209 -0.0475 1.0000 0.0337
-9.500 -0.8482 0.03912 0.03070 -0.0461 1.0000 0.0346
-9.250 -0.8364 0.03783 0.02929 -0.0447 1.0000 0.0357
-9.000 -0.8230 0.03641 0.02770 -0.0434 1.0000 0.0370
-8.750 -0.8079 0.03490 0.02599 -0.0421 1.0000 0.0382
-8.500 -0.7915 0.03343 0.02430 -0.0408 1.0000 0.0394
-8.250 -0.7741 0.03210 0.02278 -0.0394 1.0000 0.0405
-8.000 -0.7522 0.03089 0.02161 -0.0394 0.9990 0.0421
-7.750 -0.7247 0.02988 0.02055 -0.0403 0.9968 0.0447
-7.500 -0.6962 0.02888 0.01937 -0.0411 0.9947 0.0481
-7.250 -0.6697 0.02779 0.01833 -0.0418 0.9924 0.0510
-7.000 -0.6420 0.02685 0.01736 -0.0427 0.9899 0.0549
-6.750 -0.6136 0.02596 0.01645 -0.0439 0.9876 0.0603
-6.500 -0.5835 0.02524 0.01566 -0.0452 0.9857 0.0677
-6.250 -0.5543 0.02441 0.01486 -0.0467 0.9837 0.0760
-6.000 -0.5257 0.02364 0.01411 -0.0480 0.9810 0.0876
-5.750 -0.4948 0.02289 0.01341 -0.0497 0.9786 0.1044
-5.500 -0.4620 0.02207 0.01270 -0.0520 0.9765 0.1275
-5.250 -0.4275 0.02107 0.01197 -0.0548 0.9749 0.1727
-5.000 -0.3888 0.01924 0.01125 -0.0598 0.9745 0.3597
-4.750 -0.3561 0.01891 0.01143 -0.0612 0.9731 0.4788
-4.500 -0.3310 0.01910 0.01180 -0.0603 0.9701 0.5321
-4.250 -0.3049 0.01942 0.01215 -0.0597 0.9665 0.5680
-4.000 -0.2780 0.01992 0.01265 -0.0589 0.9632 0.5965
-3.750 -0.2485 0.02047 0.01313 -0.0588 0.9607 0.6220
-3.500 -0.2219 0.02109 0.01370 -0.0579 0.9581 0.6393
-3.250 -0.2000 0.02159 0.01414 -0.0563 0.9536 0.6537
-3.000 -0.1716 0.02197 0.01443 -0.0563 0.9503 0.6670
-2.750 -0.1458 0.02237 0.01479 -0.0554 0.9472 0.6725
-2.500 -0.1093 0.02236 0.01465 -0.0577 0.9453 0.6811
-2.250 -0.0839 0.02256 0.01481 -0.0573 0.9419 0.6857
-2.000 -0.0590 0.02272 0.01492 -0.0569 0.9377 0.6919
-1.750 -0.0270 0.02278 0.01491 -0.0582 0.9345 0.6994
-1.500 0.0019 0.02296 0.01507 -0.0584 0.9317 0.7039
-1.250 0.0388 0.02298 0.01502 -0.0608 0.9296 0.7112
-1.000 0.0630 0.02313 0.01517 -0.0603 0.9252 0.7156
-0.750 0.0882 0.02328 0.01532 -0.0598 0.9203 0.7201
-0.500 0.1243 0.02329 0.01530 -0.0621 0.9170 0.7272
0.000 0.1800 0.02349 0.01555 -0.0621 0.9074 0.7355
0.250 0.2138 0.02349 0.01556 -0.0637 0.9026 0.7410
0.500 0.2521 0.02343 0.01551 -0.0659 0.8990 0.7458
0.750 0.2764 0.02348 0.01563 -0.0651 0.8916 0.7494
1.000 0.3107 0.02335 0.01554 -0.0663 0.8850 0.7537
1.250 0.3583 0.02296 0.01520 -0.0700 0.8801 0.7589
1.500 0.3976 0.02221 0.01451 -0.0709 0.8659 0.7625
1.750 0.4339 0.02120 0.01355 -0.0706 0.8453 0.7661
2.000 0.4667 0.02043 0.01282 -0.0702 0.8232 0.7706
2.250 0.5028 0.01991 0.01233 -0.0714 0.8044 0.7759
2.500 0.5294 0.01958 0.01208 -0.0703 0.7859 0.7791
2.750 0.5507 0.01944 0.01204 -0.0686 0.7619 0.7827
3.000 0.5789 0.01915 0.01179 -0.0681 0.7275 0.7865
3.250 0.6258 0.01850 0.01076 -0.0703 0.6160 0.7901
3.500 0.6489 0.01933 0.01054 -0.0687 0.4455 0.7936
3.750 0.6614 0.02033 0.01093 -0.0660 0.3345 0.7970
4.000 0.6794 0.02119 0.01134 -0.0645 0.2570 0.8007
4.250 0.7022 0.02191 0.01180 -0.0642 0.2109 0.8043
4.500 0.7268 0.02255 0.01227 -0.0641 0.1836 0.8079
4.750 0.7469 0.02306 0.01270 -0.0629 0.1670 0.8106
5.000 0.7688 0.02356 0.01320 -0.0620 0.1546 0.8136
5.250 0.7914 0.02414 0.01372 -0.0614 0.1455 0.8168
5.500 0.8164 0.02470 0.01431 -0.0613 0.1379 0.8202
6.000 0.8619 0.02592 0.01558 -0.0601 0.1275 0.8259
6.250 0.8848 0.02652 0.01623 -0.0594 0.1230 0.8287
6.500 0.9085 0.02724 0.01692 -0.0591 0.1189 0.8318
6.750 0.9346 0.02801 0.01774 -0.0592 0.1147 0.8350
7.000 0.9617 0.02873 0.01855 -0.0596 0.1101 0.8378
7.250 0.9843 0.02939 0.01926 -0.0589 0.1064 0.8403
7.500 1.0083 0.03029 0.02012 -0.0586 0.1032 0.8430
7.750 1.0341 0.03114 0.02114 -0.0586 0.1001 0.8459
8.000 1.0597 0.03197 0.02214 -0.0586 0.0962 0.8488
8.250 1.0847 0.03280 0.02303 -0.0587 0.0924 0.8517
8.500 1.1070 0.03373 0.02395 -0.0583 0.0893 0.8542
8.750 1.1298 0.03476 0.02521 -0.0577 0.0865 0.8568
9.000 1.1529 0.03588 0.02658 -0.0573 0.0837 0.8594
9.250 1.1757 0.03704 0.02792 -0.0570 0.0809 0.8619
9.500 1.1983 0.03821 0.02920 -0.0568 0.0786 0.8647
9.750 1.2215 0.03958 0.03056 -0.0568 0.0764 0.8674
10.000 1.2367 0.04104 0.03240 -0.0551 0.0738 0.8700
10.250 1.2505 0.04242 0.03412 -0.0535 0.0708 0.8728
10.500 1.2649 0.04359 0.03547 -0.0521 0.0683 0.8756
10.750 1.2808 0.04453 0.03645 -0.0511 0.0662 0.8783
11.000 1.2933 0.04612 0.03823 -0.0497 0.0641 0.8809
11.250 1.2954 0.04808 0.04062 -0.0466 0.0619 0.8836
11.500 1.2977 0.04976 0.04259 -0.0438 0.0600 0.8868
11.750 1.3025 0.05124 0.04425 -0.0415 0.0583 0.8902
12.000 1.3095 0.05261 0.04572 -0.0398 0.0570 0.8936
12.250 1.3195 0.05392 0.04701 -0.0385 0.0557 0.8967
12.500 1.3046 0.05730 0.05089 -0.0351 0.0544 0.8995
12.750 1.2884 0.06097 0.05500 -0.0323 0.0531 0.9025
13.000 1.2716 0.06487 0.05926 -0.0304 0.0520 0.9056
13.250 1.2544 0.06904 0.06372 -0.0292 0.0511 0.9087
13.500 1.2359 0.07350 0.06845 -0.0287 0.0503 0.9119
13.750 1.2128 0.07892 0.07414 -0.0293 0.0498 0.9150
14.000 1.1701 0.08810 0.08368 -0.0325 0.0499 0.9172
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