NACA 642-015 AIRFOIL (n64015-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 642-015 AIRFOIL (n64015-il) Reynolds number: 200,000 Max Cl/Cd: 48.85 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64015-il-200000.txt Download as CSV file: xf-n64015-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 642-015 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7315 0.09111 0.08743 -0.0265 1.0000 0.0465
-13.750 -0.7239 0.08683 0.08314 -0.0267 1.0000 0.0452
-13.500 -0.8633 0.08080 0.07661 -0.0310 1.0000 0.0452
-13.250 -0.8831 0.07497 0.07066 -0.0331 1.0000 0.0446
-13.000 -0.9058 0.06941 0.06494 -0.0347 1.0000 0.0439
-12.750 -0.9298 0.06418 0.05951 -0.0355 1.0000 0.0431
-12.500 -0.9561 0.05913 0.05419 -0.0353 1.0000 0.0421
-12.250 -1.0083 0.05275 0.04719 -0.0327 1.0000 0.0402
-12.000 -1.0342 0.04944 0.04345 -0.0291 1.0000 0.0396
-11.750 -1.0406 0.04690 0.04061 -0.0263 1.0000 0.0393
-11.500 -1.0368 0.04412 0.03758 -0.0245 1.0000 0.0394
-11.250 -1.0267 0.04134 0.03459 -0.0235 1.0000 0.0396
-11.000 -1.0122 0.03887 0.03195 -0.0227 1.0000 0.0400
-10.750 -0.9954 0.03699 0.02997 -0.0221 1.0000 0.0408
-10.500 -0.9774 0.03556 0.02849 -0.0215 1.0000 0.0421
-10.250 -0.9594 0.03384 0.02658 -0.0208 1.0000 0.0431
-10.000 -0.9390 0.03205 0.02460 -0.0202 1.0000 0.0440
-9.750 -0.9168 0.03044 0.02281 -0.0198 1.0000 0.0450
-9.500 -0.8948 0.02914 0.02132 -0.0193 1.0000 0.0459
-9.250 -0.8623 0.02702 0.01919 -0.0203 1.0000 0.0476
-9.000 -0.8386 0.02588 0.01811 -0.0203 1.0000 0.0498
-8.750 -0.8177 0.02496 0.01717 -0.0197 1.0000 0.0523
-8.500 -0.7959 0.02405 0.01620 -0.0192 1.0000 0.0544
-8.250 -0.7756 0.02270 0.01489 -0.0186 1.0000 0.0570
-8.000 -0.7630 0.02188 0.01415 -0.0170 1.0000 0.0595
-7.750 -0.7642 0.02151 0.01379 -0.0131 0.9986 0.0620
-7.500 -0.7285 0.02023 0.01251 -0.0160 0.9864 0.0677
-7.250 -0.6929 0.01916 0.01144 -0.0188 0.9755 0.0752
-7.000 -0.6623 0.01797 0.01029 -0.0208 0.9631 0.0869
-6.750 -0.6390 0.01678 0.00922 -0.0213 0.9488 0.1077
-6.500 -0.6292 0.01537 0.00822 -0.0194 0.9323 0.1689
-6.250 -0.6305 0.01368 0.00730 -0.0155 0.9160 0.3045
-6.000 -0.6248 0.01279 0.00711 -0.0120 0.9024 0.4478
-5.750 -0.6053 0.01277 0.00714 -0.0101 0.8920 0.5002
-5.500 -0.5837 0.01283 0.00716 -0.0086 0.8824 0.5290
-5.250 -0.5605 0.01293 0.00716 -0.0075 0.8721 0.5512
-5.000 -0.5373 0.01304 0.00717 -0.0062 0.8641 0.5686
-4.750 -0.5121 0.01316 0.00725 -0.0054 0.8545 0.5836
-4.500 -0.4874 0.01333 0.00737 -0.0043 0.8472 0.5981
-4.250 -0.4616 0.01354 0.00758 -0.0035 0.8381 0.6127
-4.000 -0.4363 0.01376 0.00776 -0.0025 0.8312 0.6255
-3.750 -0.4102 0.01395 0.00792 -0.0018 0.8221 0.6382
-3.250 -0.3575 0.01433 0.00827 -0.0003 0.8071 0.6594
-3.000 -0.3317 0.01425 0.00803 0.0001 0.8008 0.6671
-2.750 -0.3037 0.01422 0.00801 0.0002 0.7932 0.6712
-2.500 -0.2765 0.01416 0.00788 0.0003 0.7865 0.6761
-2.250 -0.2497 0.01405 0.00764 0.0003 0.7804 0.6824
-2.000 -0.2219 0.01400 0.00760 0.0004 0.7728 0.6865
-1.750 -0.1946 0.01397 0.00751 0.0007 0.7672 0.6914
-1.500 -0.1670 0.01391 0.00739 0.0004 0.7602 0.6974
-1.250 -0.1393 0.01382 0.00727 0.0004 0.7541 0.7017
-1.000 -0.1116 0.01380 0.00721 0.0006 0.7495 0.7059
-0.750 -0.0836 0.01379 0.00721 0.0003 0.7426 0.7114
-0.500 -0.0557 0.01371 0.00708 0.0001 0.7371 0.7169
-0.250 -0.0279 0.01370 0.00704 0.0002 0.7328 0.7208
0.000 0.0000 0.01372 0.00712 0.0000 0.7260 0.7260
0.250 0.0279 0.01370 0.00704 -0.0002 0.7208 0.7328
0.500 0.0558 0.01371 0.00708 -0.0001 0.7169 0.7371
0.750 0.0836 0.01379 0.00721 -0.0003 0.7113 0.7426
1.000 0.1116 0.01380 0.00721 -0.0006 0.7059 0.7495
1.250 0.1393 0.01382 0.00727 -0.0004 0.7017 0.7541
1.500 0.1670 0.01391 0.00739 -0.0004 0.6974 0.7602
1.750 0.1946 0.01397 0.00751 -0.0007 0.6914 0.7672
2.000 0.2219 0.01400 0.00760 -0.0004 0.6865 0.7728
2.250 0.2498 0.01405 0.00764 -0.0003 0.6824 0.7804
2.500 0.2765 0.01416 0.00788 -0.0004 0.6761 0.7865
2.750 0.3038 0.01422 0.00801 -0.0002 0.6711 0.7933
3.000 0.3317 0.01425 0.00803 -0.0001 0.6671 0.8008
3.250 0.3575 0.01433 0.00827 0.0002 0.6594 0.8071
3.750 0.4102 0.01395 0.00793 0.0017 0.6382 0.8221
4.000 0.4363 0.01376 0.00776 0.0025 0.6255 0.8312
4.250 0.4617 0.01354 0.00758 0.0035 0.6126 0.8381
4.500 0.4874 0.01333 0.00737 0.0043 0.5980 0.8472
4.750 0.5122 0.01316 0.00725 0.0054 0.5836 0.8545
5.000 0.5373 0.01304 0.00716 0.0062 0.5685 0.8641
5.250 0.5605 0.01293 0.00716 0.0075 0.5514 0.8721
5.500 0.5837 0.01283 0.00716 0.0086 0.5290 0.8824
5.750 0.6054 0.01276 0.00713 0.0101 0.5000 0.8920
6.000 0.6248 0.01279 0.00711 0.0120 0.4475 0.9025
6.250 0.6306 0.01368 0.00730 0.0155 0.3049 0.9160
6.500 0.6291 0.01538 0.00822 0.0194 0.1684 0.9324
6.750 0.6391 0.01678 0.00922 0.0213 0.1076 0.9488
7.000 0.6624 0.01797 0.01029 0.0208 0.0870 0.9631
7.250 0.6931 0.01916 0.01144 0.0188 0.0752 0.9755
7.500 0.7286 0.02023 0.01251 0.0160 0.0676 0.9865
7.750 0.7644 0.02152 0.01380 0.0131 0.0618 0.9987
8.000 0.7630 0.02188 0.01415 0.0170 0.0594 1.0000
8.250 0.7757 0.02272 0.01491 0.0186 0.0569 1.0000
8.500 0.7961 0.02406 0.01620 0.0192 0.0544 1.0000
8.750 0.8179 0.02496 0.01717 0.0197 0.0523 1.0000
9.000 0.8392 0.02590 0.01813 0.0202 0.0499 1.0000
9.250 0.8624 0.02701 0.01918 0.0203 0.0477 1.0000
9.500 0.8945 0.02912 0.02130 0.0193 0.0459 1.0000
9.750 0.9167 0.03043 0.02279 0.0198 0.0449 1.0000
10.000 0.9390 0.03206 0.02462 0.0203 0.0439 1.0000
10.250 0.9595 0.03383 0.02657 0.0208 0.0431 1.0000
10.500 0.9776 0.03555 0.02848 0.0215 0.0421 1.0000
10.750 0.9954 0.03705 0.03005 0.0221 0.0409 1.0000
11.000 1.0124 0.03892 0.03200 0.0227 0.0400 1.0000
11.250 1.0278 0.04145 0.03467 0.0233 0.0394 1.0000
11.500 1.0373 0.04419 0.03765 0.0245 0.0393 1.0000
11.750 1.0417 0.04713 0.04084 0.0260 0.0392 1.0000
12.000 1.0347 0.04947 0.04348 0.0290 0.0395 1.0000
12.250 0.9934 0.05364 0.04825 0.0335 0.0408 1.0000
12.500 0.9561 0.05920 0.05426 0.0353 0.0421 1.0000
12.750 0.9293 0.06433 0.05966 0.0354 0.0431 1.0000
13.000 0.9056 0.06950 0.06504 0.0346 0.0439 1.0000
13.250 0.8832 0.07505 0.07074 0.0330 0.0446 1.0000
13.500 0.8639 0.08092 0.07673 0.0309 0.0453 1.0000
13.750 0.7233 0.08667 0.08299 0.0268 0.0452 1.0000
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