USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 29 AIRFOIL (usa29-il) Reynolds number: 200,000 Max Cl/Cd: 72.64 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa29-il-200000-n5.txt Download as CSV file: xf-usa29-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 29 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2750 0.10157 0.09795 -0.0649 0.9850 0.0345
-10.750 -0.2743 0.09549 0.09186 -0.0695 0.9805 0.0363
-10.500 -0.2985 0.08364 0.08002 -0.0782 0.9749 0.0384
-10.250 -0.2736 0.08297 0.07933 -0.0803 0.9720 0.0393
-10.000 -0.2597 0.08101 0.07737 -0.0822 0.9661 0.0403
-9.500 -0.4112 0.03818 0.03381 -0.1173 0.9318 0.0425
-9.250 -0.4100 0.03494 0.03017 -0.1167 0.9226 0.0436
-9.000 -0.3986 0.03227 0.02706 -0.1166 0.9161 0.0450
-8.750 -0.3891 0.03038 0.02478 -0.1149 0.9080 0.0458
-8.500 -0.3719 0.02888 0.02289 -0.1141 0.9016 0.0465
-8.250 -0.3572 0.02680 0.02059 -0.1129 0.8952 0.0476
-8.000 -0.3385 0.02561 0.01928 -0.1118 0.8880 0.0486
-7.750 -0.3126 0.02442 0.01792 -0.1120 0.8835 0.0495
-7.500 -0.2960 0.02350 0.01682 -0.1102 0.8748 0.0502
-7.250 -0.2704 0.02242 0.01554 -0.1101 0.8694 0.0510
-7.000 -0.2503 0.02160 0.01454 -0.1088 0.8611 0.0519
-6.750 -0.2242 0.02071 0.01345 -0.1086 0.8547 0.0529
-6.500 -0.2021 0.02002 0.01259 -0.1076 0.8464 0.0541
-6.250 -0.1752 0.01930 0.01168 -0.1074 0.8393 0.0551
-6.000 -0.1522 0.01869 0.01093 -0.1065 0.8303 0.0558
-5.750 -0.1245 0.01806 0.01013 -0.1064 0.8228 0.0565
-5.500 -0.1016 0.01757 0.00951 -0.1054 0.8128 0.0570
-5.250 -0.0769 0.01683 0.00869 -0.1048 0.8040 0.0581
-5.000 -0.0533 0.01630 0.00810 -0.1039 0.7938 0.0593
-4.750 -0.0299 0.01588 0.00760 -0.1030 0.7831 0.0605
-4.500 -0.0048 0.01550 0.00714 -0.1024 0.7727 0.0621
-4.250 0.0195 0.01519 0.00673 -0.1016 0.7611 0.0640
-4.000 0.0434 0.01490 0.00636 -0.1007 0.7486 0.0659
-3.750 0.0679 0.01465 0.00599 -0.0999 0.7363 0.0675
-3.500 0.0925 0.01440 0.00565 -0.0991 0.7237 0.0696
-3.250 0.1175 0.01416 0.00536 -0.0985 0.7110 0.0729
-3.000 0.1424 0.01398 0.00510 -0.0978 0.6985 0.0772
-2.750 0.1671 0.01381 0.00489 -0.0971 0.6863 0.0857
-2.500 0.1921 0.01366 0.00469 -0.0964 0.6752 0.0997
-2.250 0.2173 0.01351 0.00447 -0.0959 0.6652 0.1166
-2.000 0.2420 0.01335 0.00432 -0.0952 0.6555 0.1357
-1.750 0.2669 0.01321 0.00424 -0.0947 0.6467 0.1653
-1.500 0.2919 0.01316 0.00418 -0.0941 0.6382 0.1946
-1.250 0.3168 0.01313 0.00414 -0.0935 0.6305 0.2146
-1.000 0.3415 0.01313 0.00412 -0.0928 0.6230 0.2325
-0.750 0.3661 0.01316 0.00417 -0.0922 0.6162 0.2541
-0.500 0.3904 0.01322 0.00425 -0.0914 0.6090 0.2739
-0.250 0.4154 0.01335 0.00432 -0.0908 0.6029 0.2915
0.000 0.4397 0.01345 0.00443 -0.0900 0.5964 0.3069
0.250 0.4642 0.01360 0.00451 -0.0893 0.5902 0.3204
0.500 0.4887 0.01375 0.00462 -0.0886 0.5845 0.3325
0.750 0.5123 0.01389 0.00473 -0.0877 0.5780 0.3436
1.000 0.5369 0.01404 0.00480 -0.0870 0.5727 0.3530
1.250 0.5609 0.01413 0.00489 -0.0862 0.5670 0.3600
1.500 0.5848 0.01423 0.00494 -0.0854 0.5611 0.3666
1.750 0.6095 0.01431 0.00499 -0.0848 0.5558 0.3716
2.000 0.6333 0.01438 0.00507 -0.0840 0.5503 0.3769
2.250 0.6573 0.01445 0.00513 -0.0832 0.5448 0.3815
2.500 0.6816 0.01453 0.00519 -0.0826 0.5398 0.3870
2.750 0.7047 0.01462 0.00529 -0.0817 0.5341 0.3932
3.000 0.7282 0.01466 0.00538 -0.0809 0.5286 0.3986
3.250 0.7523 0.01475 0.00545 -0.0802 0.5240 0.4039
3.750 0.7980 0.01488 0.00567 -0.0783 0.5131 0.4117
4.000 0.8213 0.01497 0.00577 -0.0775 0.5086 0.4162
4.250 0.8436 0.01506 0.00592 -0.0765 0.5034 0.4216
4.500 0.8651 0.01511 0.00605 -0.0753 0.4980 0.4271
4.750 0.8874 0.01521 0.00618 -0.0743 0.4934 0.4331
5.000 0.9092 0.01532 0.00635 -0.0732 0.4885 0.4379
5.250 0.9303 0.01542 0.00653 -0.0720 0.4833 0.4424
5.500 0.9524 0.01555 0.00670 -0.0709 0.4787 0.4468
5.750 0.9742 0.01570 0.00690 -0.0699 0.4738 0.4518
6.000 0.9953 0.01584 0.00714 -0.0687 0.4687 0.4587
6.500 1.0401 0.01613 0.00761 -0.0670 0.4594 0.4858
7.000 1.2000 0.01652 0.00911 -0.0910 0.4253 0.9957
7.250 1.2251 0.01687 0.00946 -0.0909 0.4118 1.0000
7.500 1.2319 0.01715 0.00972 -0.0869 0.4003 1.0000
7.750 1.2362 0.01745 0.01002 -0.0824 0.3859 1.0000
8.000 1.2427 0.01781 0.01039 -0.0785 0.3720 1.0000
8.250 1.2472 0.01826 0.01081 -0.0744 0.3551 1.0000
8.500 1.2494 0.01886 0.01134 -0.0700 0.3316 1.0000
8.750 1.2460 0.01975 0.01207 -0.0650 0.2989 1.0000
9.000 1.2359 0.02109 0.01316 -0.0594 0.2549 1.0000
9.250 1.2206 0.02297 0.01471 -0.0536 0.2034 1.0000
9.500 1.1917 0.02593 0.01719 -0.0470 0.1313 1.0000
9.750 1.1634 0.02929 0.02015 -0.0413 0.0608 1.0000
10.000 1.1524 0.03180 0.02254 -0.0378 0.0387 1.0000
10.250 1.1512 0.03375 0.02452 -0.0354 0.0327 1.0000
10.500 1.1533 0.03554 0.02639 -0.0335 0.0297 1.0000
10.750 1.1560 0.03735 0.02831 -0.0317 0.0279 1.0000
11.000 1.1560 0.03950 0.03056 -0.0301 0.0260 1.0000
11.250 1.1544 0.04190 0.03305 -0.0285 0.0247 1.0000
11.500 1.1558 0.04412 0.03538 -0.0273 0.0233 1.0000
11.750 1.1563 0.04651 0.03789 -0.0262 0.0226 1.0000
12.000 1.1574 0.04891 0.04039 -0.0253 0.0216 1.0000
12.250 1.1559 0.05168 0.04327 -0.0244 0.0207 1.0000
12.500 1.1540 0.05455 0.04623 -0.0237 0.0204 1.0000
12.750 1.1502 0.05770 0.04948 -0.0231 0.0198 1.0000
13.000 1.1467 0.06088 0.05276 -0.0226 0.0194 1.0000
13.250 1.1382 0.06472 0.05668 -0.0222 0.0187 1.0000
13.500 1.1363 0.06781 0.05986 -0.0218 0.0182 1.0000
13.750 1.1336 0.07103 0.06317 -0.0215 0.0181 1.0000
14.000 1.1352 0.07379 0.06602 -0.0213 0.0172 1.0000
14.250 1.1340 0.07686 0.06916 -0.0210 0.0169 1.0000
14.500 1.1351 0.07967 0.07205 -0.0209 0.0162 1.0000
14.750 1.1360 0.08249 0.07492 -0.0207 0.0159 1.0000
15.000 1.1380 0.08517 0.07766 -0.0204 0.0155 1.0000
15.250 1.1405 0.08777 0.08030 -0.0202 0.0151 1.0000
15.500 1.1436 0.09024 0.08281 -0.0199 0.0148 1.0000
15.750 1.1476 0.09252 0.08513 -0.0195 0.0144 1.0000
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