NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(2)-415 (naca652415-il) Reynolds number: 100,000 Max Cl/Cd: 46.67 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca652415-il-100000.txt Download as CSV file: xf-naca652415-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4552 0.10131 0.09661 -0.0570 1.0000 0.1604
-10.250 -0.4085 0.09876 0.09396 -0.0514 1.0000 0.1648
-10.000 -0.4145 0.09699 0.09229 -0.0493 1.0000 0.1719
-9.750 -0.4730 0.09522 0.09075 -0.0480 1.0000 0.1751
-9.500 -0.5355 0.09322 0.08896 -0.0462 1.0000 0.1757
-9.250 -0.4696 0.09255 0.08817 -0.0395 1.0000 0.1850
-9.000 -0.5078 0.09071 0.08648 -0.0372 1.0000 0.1885
-8.750 -0.5617 0.08789 0.08383 -0.0362 1.0000 0.1899
-8.500 -0.5455 0.08675 0.08269 -0.0318 0.9999 0.1979
-8.250 -0.6319 0.07788 0.07364 -0.0475 0.9816 0.2071
-7.250 -0.6194 0.04488 0.03746 -0.0555 0.9519 0.0853
-7.000 -0.5970 0.04139 0.03370 -0.0559 0.9465 0.0831
-6.750 -0.5656 0.03831 0.03017 -0.0574 0.9425 0.0810
-6.500 -0.5434 0.03631 0.02780 -0.0569 0.9369 0.0807
-6.250 -0.5187 0.03480 0.02597 -0.0568 0.9315 0.0827
-6.000 -0.4844 0.03320 0.02404 -0.0581 0.9277 0.0841
-5.750 -0.4521 0.03189 0.02248 -0.0590 0.9237 0.0852
-5.500 -0.4323 0.03095 0.02137 -0.0576 0.9173 0.0868
-5.250 -0.4005 0.02951 0.02009 -0.0587 0.9135 0.0917
-5.000 -0.3638 0.02862 0.01917 -0.0604 0.9105 0.0974
-4.750 -0.3499 0.02823 0.01871 -0.0581 0.9043 0.1007
-4.500 -0.3280 0.02734 0.01801 -0.0576 0.8991 0.1079
-4.250 -0.2965 0.02652 0.01730 -0.0587 0.8954 0.1230
-3.750 -0.2807 0.02320 0.01652 -0.0542 0.8848 0.5403
-3.500 -0.2614 0.02459 0.01806 -0.0499 0.8802 0.6695
-3.250 -0.2434 0.02571 0.01914 -0.0463 0.8755 0.7028
-3.000 -0.2377 0.02656 0.01996 -0.0415 0.8693 0.7232
-2.750 -0.2222 0.02760 0.02096 -0.0374 0.8651 0.7491
-2.500 -0.2096 0.02932 0.02273 -0.0299 0.8618 0.7838
-2.250 -0.2218 0.03019 0.02363 -0.0213 0.8547 0.8053
-2.000 -0.2143 0.03109 0.02450 -0.0151 0.8504 0.8310
-1.750 -0.1885 0.03131 0.02459 -0.0144 0.8473 0.8445
-1.500 -0.1715 0.03146 0.02463 -0.0130 0.8430 0.8523
-1.250 -0.1665 0.03142 0.02452 -0.0103 0.8372 0.8609
-1.000 -0.1427 0.03150 0.02450 -0.0103 0.8336 0.8673
-0.750 -0.1115 0.03150 0.02436 -0.0120 0.8306 0.8742
-0.500 -0.1037 0.03166 0.02449 -0.0095 0.8254 0.8806
-0.250 -0.0922 0.03175 0.02451 -0.0081 0.8207 0.8887
0.000 -0.0661 0.03190 0.02460 -0.0086 0.8172 0.8943
0.250 -0.0293 0.03205 0.02466 -0.0107 0.8142 0.9001
0.500 -0.0280 0.03230 0.02489 -0.0079 0.8087 0.9084
0.750 -0.0121 0.03254 0.02510 -0.0072 0.8044 0.9165
1.000 0.0197 0.03275 0.02525 -0.0086 0.8005 0.9230
1.250 0.0618 0.03303 0.02549 -0.0116 0.7976 0.9286
1.500 0.0618 0.03350 0.02596 -0.0091 0.7915 0.9390
1.750 0.0888 0.03383 0.02628 -0.0103 0.7867 0.9477
2.000 0.1353 0.03423 0.02666 -0.0143 0.7832 0.9531
2.250 0.1604 0.03484 0.02729 -0.0158 0.7775 0.9618
2.500 0.1976 0.03547 0.02794 -0.0193 0.7718 0.9689
2.750 0.2503 0.03587 0.02836 -0.0244 0.7677 0.9741
3.000 0.2866 0.03668 0.02922 -0.0282 0.7612 0.9809
3.250 0.3305 0.03729 0.02988 -0.0327 0.7549 0.9869
3.500 0.3896 0.03754 0.03019 -0.0385 0.7511 0.9914
3.750 0.3863 0.03835 0.03104 -0.0364 0.7415 1.0000
4.000 0.4073 0.03831 0.03102 -0.0358 0.7361 1.0000
4.250 0.4019 0.03898 0.03169 -0.0328 0.7264 1.0000
4.500 0.4417 0.03910 0.03186 -0.0351 0.7206 1.0000
4.750 0.4557 0.03995 0.03276 -0.0349 0.7105 1.0000
5.000 0.4996 0.03996 0.03285 -0.0375 0.7047 1.0000
5.250 0.5160 0.04082 0.03376 -0.0375 0.6936 1.0000
5.500 0.5671 0.04037 0.03344 -0.0402 0.6883 1.0000
5.750 0.5841 0.04110 0.03424 -0.0399 0.6758 1.0000
6.000 0.6363 0.04026 0.03355 -0.0422 0.6701 1.0000
6.250 0.6640 0.04025 0.03366 -0.0424 0.6582 1.0000
6.500 0.6910 0.04022 0.03376 -0.0423 0.6457 1.0000
6.750 0.8632 0.02704 0.02102 -0.0481 0.6323 1.0000
7.000 0.9453 0.02210 0.01624 -0.0511 0.6087 1.0000
7.250 0.9651 0.02100 0.01523 -0.0485 0.5777 1.0000
7.500 0.9673 0.02074 0.01503 -0.0439 0.5354 1.0000
7.750 0.9632 0.02064 0.01416 -0.0375 0.3921 1.0000
8.000 0.9359 0.02327 0.01571 -0.0308 0.2584 1.0000
8.250 0.9117 0.02653 0.01807 -0.0259 0.1635 1.0000
8.500 0.9039 0.02910 0.02017 -0.0227 0.1250 1.0000
8.750 0.9074 0.03103 0.02191 -0.0205 0.1063 1.0000
9.000 0.9160 0.03274 0.02345 -0.0188 0.0959 1.0000
9.250 0.9322 0.03404 0.02474 -0.0177 0.0871 1.0000
9.500 0.9561 0.03535 0.02595 -0.0170 0.0801 1.0000
9.750 0.9885 0.03654 0.02711 -0.0171 0.0750 1.0000
10.000 1.0409 0.03836 0.02882 -0.0192 0.0697 1.0000
10.250 1.0738 0.04003 0.03070 -0.0197 0.0661 1.0000
10.500 1.1180 0.04241 0.03323 -0.0217 0.0637 1.0000
10.750 1.1577 0.04533 0.03636 -0.0234 0.0624 1.0000
11.000 1.1919 0.04883 0.04007 -0.0251 0.0611 1.0000
11.250 1.2204 0.05397 0.04547 -0.0265 0.0598 1.0000
11.500 1.2198 0.05618 0.04806 -0.0235 0.0595 1.0000
11.750 1.2260 0.05976 0.05195 -0.0218 0.0596 1.0000
12.000 1.2353 0.06373 0.05621 -0.0206 0.0601 1.0000
12.250 1.2238 0.06535 0.05815 -0.0166 0.0607 1.0000
12.500 1.1880 0.06766 0.06098 -0.0113 0.0621 1.0000
12.750 1.1498 0.07207 0.06588 -0.0078 0.0639 1.0000
13.000 1.1219 0.07705 0.07120 -0.0062 0.0654 1.0000
13.250 1.0969 0.08231 0.07672 -0.0056 0.0668 1.0000
13.500 1.0721 0.08793 0.08255 -0.0059 0.0680 1.0000
13.750 1.0536 0.09383 0.08861 -0.0069 0.0693 1.0000
14.000 0.8621 0.09851 0.09400 -0.0047 0.0686 1.0000
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Polar data table (+)
Polar graphs
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