NACA 65(2)-215 (naca652215-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(2)-215 (naca652215-il) Reynolds number: 100,000 Max Cl/Cd: 39.81 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652215-il-100000-n5.txt Download as CSV file: xf-naca652215-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-215
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 -0.5954 0.09141 0.08596 -0.0528 1.0000 0.0348
-12.750 -0.6241 0.08272 0.07718 -0.0584 1.0000 0.0345
-12.500 -0.6504 0.07587 0.07020 -0.0622 1.0000 0.0342
-12.250 -0.6759 0.07011 0.06430 -0.0646 1.0000 0.0340
-12.000 -0.6985 0.06533 0.05935 -0.0658 1.0000 0.0339
-11.750 -0.7191 0.06123 0.05506 -0.0660 1.0000 0.0338
-11.500 -0.7366 0.05773 0.05137 -0.0652 1.0000 0.0338
-11.250 -0.7521 0.05470 0.04814 -0.0636 1.0000 0.0338
-11.000 -0.7662 0.05211 0.04534 -0.0611 1.0000 0.0339
-10.750 -0.7808 0.04992 0.04296 -0.0575 1.0000 0.0340
-10.500 -0.7922 0.04802 0.04087 -0.0535 1.0000 0.0341
-10.250 -0.8054 0.04641 0.03908 -0.0488 1.0000 0.0343
-10.000 -0.8104 0.04454 0.03695 -0.0455 0.9962 0.0347
-9.750 -0.7926 0.04170 0.03356 -0.0466 0.9856 0.0357
-9.500 -0.7687 0.03910 0.03071 -0.0480 0.9779 0.0368
-9.250 -0.7394 0.03696 0.02839 -0.0499 0.9724 0.0378
-9.000 -0.7104 0.03497 0.02617 -0.0513 0.9656 0.0387
-8.750 -0.6776 0.03308 0.02406 -0.0532 0.9609 0.0396
-8.500 -0.6475 0.03148 0.02228 -0.0542 0.9538 0.0409
-8.250 -0.6138 0.03006 0.02065 -0.0559 0.9487 0.0429
-8.000 -0.5835 0.02876 0.01919 -0.0568 0.9418 0.0448
-7.750 -0.5524 0.02745 0.01792 -0.0580 0.9358 0.0465
-7.500 -0.5246 0.02639 0.01684 -0.0585 0.9288 0.0483
-7.250 -0.4996 0.02546 0.01584 -0.0586 0.9210 0.0503
-7.000 -0.4764 0.02471 0.01497 -0.0583 0.9131 0.0534
-6.750 -0.4580 0.02384 0.01412 -0.0574 0.9046 0.0565
-6.500 -0.4400 0.02317 0.01340 -0.0562 0.8962 0.0602
-6.250 -0.4212 0.02254 0.01264 -0.0551 0.8883 0.0643
-6.000 -0.4052 0.02185 0.01197 -0.0536 0.8804 0.0702
-5.750 -0.3876 0.02119 0.01131 -0.0523 0.8731 0.0812
-5.500 -0.3712 0.02046 0.01067 -0.0509 0.8662 0.1018
-5.250 -0.3604 0.01941 0.01000 -0.0488 0.8582 0.1668
-5.000 -0.3568 0.01780 0.00924 -0.0459 0.8513 0.3234
-4.750 -0.3488 0.01711 0.00952 -0.0424 0.8437 0.5003
-4.500 -0.3261 0.01719 0.00964 -0.0410 0.8390 0.5679
-4.250 -0.3041 0.01750 0.00992 -0.0394 0.8331 0.6085
-4.000 -0.2826 0.01830 0.01077 -0.0369 0.8272 0.6535
-3.750 -0.2576 0.01916 0.01161 -0.0346 0.8230 0.6833
-3.500 -0.2322 0.01942 0.01177 -0.0336 0.8181 0.6945
-3.250 -0.2075 0.01951 0.01174 -0.0330 0.8126 0.7014
-3.000 -0.1810 0.01950 0.01161 -0.0326 0.8083 0.7077
-2.750 -0.1551 0.01930 0.01125 -0.0325 0.8046 0.7147
-2.500 -0.1312 0.01937 0.01126 -0.0319 0.7983 0.7184
-2.250 -0.1054 0.01930 0.01111 -0.0317 0.7937 0.7232
-2.000 -0.0795 0.01908 0.01075 -0.0318 0.7902 0.7294
-1.750 -0.0540 0.01910 0.01072 -0.0315 0.7855 0.7328
-1.500 -0.0293 0.01913 0.01070 -0.0311 0.7803 0.7367
-1.250 -0.0030 0.01903 0.01053 -0.0311 0.7762 0.7414
-1.000 0.0243 0.01888 0.01028 -0.0314 0.7731 0.7468
-0.750 0.0478 0.01900 0.01041 -0.0308 0.7679 0.7502
-0.500 0.0729 0.01903 0.01042 -0.0305 0.7632 0.7541
-0.250 0.0997 0.01896 0.01030 -0.0306 0.7595 0.7592
0.000 0.1279 0.01888 0.01016 -0.0309 0.7568 0.7639
0.250 0.1497 0.01907 0.01040 -0.0302 0.7511 0.7675
0.500 0.1747 0.01912 0.01047 -0.0299 0.7467 0.7720
0.750 0.2020 0.01908 0.01040 -0.0301 0.7433 0.7776
1.000 0.2304 0.01907 0.01039 -0.0302 0.7407 0.7815
1.250 0.2506 0.01933 0.01073 -0.0293 0.7347 0.7857
1.500 0.2756 0.01941 0.01084 -0.0291 0.7303 0.7909
1.750 0.3030 0.01942 0.01087 -0.0293 0.7271 0.7963
2.000 0.3315 0.01944 0.01093 -0.0293 0.7247 0.8002
2.250 0.3495 0.01978 0.01138 -0.0282 0.7180 0.8058
2.500 0.3751 0.01988 0.01152 -0.0282 0.7138 0.8118
2.750 0.4023 0.01992 0.01165 -0.0280 0.7107 0.8159
3.000 0.4266 0.02008 0.01189 -0.0276 0.7065 0.8216
3.250 0.4466 0.02038 0.01229 -0.0268 0.7002 0.8283
3.500 0.4731 0.02042 0.01244 -0.0264 0.6961 0.8330
3.750 0.5038 0.02031 0.01241 -0.0267 0.6930 0.8385
4.000 0.5191 0.02070 0.01294 -0.0251 0.6842 0.8457
4.250 0.5474 0.02060 0.01296 -0.0249 0.6794 0.8514
4.500 0.5696 0.02071 0.01320 -0.0241 0.6721 0.8592
4.750 0.5954 0.02056 0.01318 -0.0233 0.6645 0.8648
5.000 0.6185 0.02043 0.01320 -0.0222 0.6544 0.8724
5.250 0.6452 0.01977 0.01263 -0.0209 0.6381 0.8792
5.500 0.6686 0.01879 0.01165 -0.0187 0.6079 0.8873
5.750 0.6862 0.01824 0.01111 -0.0159 0.5704 0.8961
6.000 0.7024 0.01810 0.01102 -0.0136 0.5350 0.9068
6.250 0.7182 0.01804 0.01086 -0.0110 0.4744 0.9175
6.500 0.7244 0.01858 0.01072 -0.0072 0.3592 0.9312
6.750 0.7206 0.02001 0.01153 -0.0032 0.2538 0.9504
7.000 0.7252 0.02188 0.01279 -0.0017 0.1517 0.9731
7.250 0.7330 0.02331 0.01384 -0.0006 0.0994 1.0000
7.500 0.7405 0.02446 0.01481 0.0012 0.0788 1.0000
7.750 0.7512 0.02558 0.01583 0.0025 0.0684 1.0000
8.000 0.7636 0.02665 0.01692 0.0037 0.0614 1.0000
8.250 0.7750 0.02783 0.01808 0.0048 0.0571 1.0000
8.500 0.7883 0.02891 0.01923 0.0058 0.0527 1.0000
8.750 0.8001 0.03014 0.02044 0.0069 0.0496 1.0000
9.000 0.8129 0.03139 0.02172 0.0079 0.0474 1.0000
9.250 0.8282 0.03255 0.02295 0.0088 0.0456 1.0000
9.500 0.8444 0.03374 0.02420 0.0096 0.0435 1.0000
9.750 0.8612 0.03493 0.02538 0.0102 0.0417 1.0000
10.000 0.8798 0.03630 0.02667 0.0107 0.0397 1.0000
10.250 0.9014 0.03749 0.02801 0.0112 0.0382 1.0000
10.500 0.9252 0.03885 0.02952 0.0114 0.0370 1.0000
10.750 0.9492 0.04034 0.03113 0.0116 0.0360 1.0000
11.000 0.9719 0.04200 0.03293 0.0118 0.0350 1.0000
11.250 0.9912 0.04372 0.03476 0.0121 0.0341 1.0000
11.500 1.0088 0.04553 0.03665 0.0124 0.0331 1.0000
11.750 1.0276 0.04779 0.03899 0.0125 0.0323 1.0000
12.000 1.0330 0.05002 0.04157 0.0138 0.0317 1.0000
12.250 1.0365 0.05255 0.04442 0.0149 0.0311 1.0000
12.500 1.0376 0.05539 0.04757 0.0160 0.0308 1.0000
12.750 1.0345 0.05851 0.05098 0.0171 0.0305 1.0000
13.000 1.0284 0.06184 0.05460 0.0179 0.0303 1.0000
13.250 1.0183 0.06556 0.05861 0.0185 0.0302 1.0000
13.500 1.0059 0.06957 0.06288 0.0186 0.0301 1.0000
13.750 0.9894 0.07415 0.06773 0.0183 0.0300 1.0000
14.000 0.9705 0.07922 0.07305 0.0173 0.0301 1.0000
14.250 0.9492 0.08491 0.07898 0.0156 0.0301 1.0000
14.500 0.9242 0.09156 0.08586 0.0128 0.0302 1.0000
14.750 0.8974 0.09924 0.09376 0.0088 0.0304 1.0000
15.000 0.8664 0.10879 0.10350 0.0031 0.0307 1.0000
15.250 0.8338 0.12045 0.11530 -0.0044 0.0311 1.0000
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