NACA 0010-65 (naca001065-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-65 (naca001065-il) Reynolds number: 200,000 Max Cl/Cd: 40.59 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001065-il-200000.txt Download as CSV file: xf-naca001065-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-65
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5137 0.09092 0.08732 -0.0346 1.0000 0.0742
-10.250 -0.5373 0.08404 0.08049 -0.0384 1.0000 0.0754
-10.000 -0.5637 0.07680 0.07328 -0.0422 1.0000 0.0753
-9.750 -0.5907 0.07112 0.06759 -0.0433 1.0000 0.0751
-9.500 -0.6207 0.06666 0.06309 -0.0418 1.0000 0.0750
-9.250 -0.6508 0.06331 0.05970 -0.0380 1.0000 0.0749
-9.000 -0.6812 0.06086 0.05721 -0.0322 1.0000 0.0749
-8.750 -0.7190 0.05869 0.05486 -0.0252 1.0000 0.0761
-8.500 -0.7552 0.05764 0.05348 -0.0172 1.0000 0.0771
-8.250 -0.7712 0.05532 0.05091 -0.0116 1.0000 0.0773
-8.000 -0.8333 0.05796 0.05306 -0.0052 1.0000 0.0783
-7.750 -0.8491 0.04562 0.03989 0.0025 1.0000 0.0519
-7.500 -0.8486 0.04144 0.03544 0.0064 1.0000 0.0512
-7.250 -0.8453 0.03778 0.03145 0.0103 1.0000 0.0504
-7.000 -0.8386 0.03444 0.02771 0.0140 1.0000 0.0499
-6.750 -0.8278 0.03172 0.02457 0.0172 1.0000 0.0502
-6.500 -0.8134 0.03014 0.02259 0.0200 1.0000 0.0517
-6.250 -0.7977 0.02860 0.02068 0.0224 1.0000 0.0527
-6.000 -0.7778 0.02568 0.01747 0.0238 1.0000 0.0537
-5.750 -0.7568 0.02427 0.01597 0.0248 1.0000 0.0556
-5.500 -0.7358 0.02343 0.01505 0.0260 1.0000 0.0581
-5.250 -0.7132 0.02242 0.01389 0.0271 1.0000 0.0599
-5.000 -0.6901 0.02146 0.01278 0.0281 1.0000 0.0615
-4.750 -0.6678 0.02083 0.01200 0.0292 1.0000 0.0636
-4.500 -0.6446 0.01964 0.01076 0.0301 1.0000 0.0662
-4.250 -0.6230 0.01885 0.01000 0.0311 1.0000 0.0688
-4.000 -0.6020 0.01825 0.00940 0.0324 1.0000 0.0718
-3.750 -0.5811 0.01774 0.00884 0.0337 1.0000 0.0753
-3.500 -0.5613 0.01707 0.00819 0.0351 1.0000 0.0805
-3.250 -0.5412 0.01660 0.00776 0.0365 1.0000 0.0877
-3.000 -0.5217 0.01601 0.00724 0.0380 1.0000 0.0996
-2.750 -0.5024 0.01533 0.00675 0.0395 1.0000 0.1341
-2.500 -0.4851 0.01435 0.00640 0.0410 1.0000 0.2417
-2.250 -0.4807 0.01185 0.00620 0.0454 1.0000 0.7024
-2.000 -0.4423 0.01265 0.00758 0.0457 1.0000 0.9003
-1.750 -0.3959 0.01375 0.00857 0.0431 1.0000 0.9389
-1.500 -0.2529 0.01605 0.01063 0.0213 1.0000 0.9712
-1.250 -0.1723 0.01654 0.01100 0.0105 1.0000 0.9822
-1.000 -0.0381 0.01675 0.01108 -0.0113 1.0000 1.0000
-0.750 -0.0285 0.01668 0.01100 -0.0085 1.0000 1.0000
-0.500 -0.0190 0.01663 0.01094 -0.0057 1.0000 1.0000
-0.250 -0.0095 0.01660 0.01090 -0.0028 1.0000 1.0000
0.000 0.0000 0.01659 0.01089 0.0000 1.0000 1.0000
0.250 0.0095 0.01660 0.01090 0.0028 1.0000 1.0000
0.500 0.0190 0.01663 0.01094 0.0057 1.0000 1.0000
0.750 0.0285 0.01668 0.01100 0.0085 1.0000 1.0000
1.000 0.0381 0.01675 0.01108 0.0113 1.0000 1.0000
1.250 0.1722 0.01654 0.01100 -0.0105 0.9823 1.0000
1.500 0.2526 0.01605 0.01063 -0.0213 0.9712 1.0000
1.750 0.3959 0.01374 0.00857 -0.0431 0.9389 1.0000
2.000 0.4422 0.01265 0.00758 -0.0457 0.9004 1.0000
2.250 0.4806 0.01184 0.00621 -0.0454 0.7056 1.0000
2.500 0.4850 0.01435 0.00640 -0.0410 0.2415 1.0000
2.750 0.5024 0.01533 0.00675 -0.0395 0.1346 1.0000
3.000 0.5216 0.01601 0.00723 -0.0380 0.0996 1.0000
3.250 0.5411 0.01660 0.00775 -0.0365 0.0878 1.0000
3.500 0.5612 0.01707 0.00819 -0.0351 0.0805 1.0000
3.750 0.5810 0.01774 0.00883 -0.0337 0.0753 1.0000
4.000 0.6019 0.01825 0.00940 -0.0324 0.0717 1.0000
4.250 0.6229 0.01884 0.01000 -0.0311 0.0688 1.0000
4.500 0.6445 0.01963 0.01076 -0.0300 0.0662 1.0000
4.750 0.6677 0.02083 0.01199 -0.0292 0.0636 1.0000
5.000 0.6900 0.02146 0.01278 -0.0281 0.0616 1.0000
5.250 0.7131 0.02242 0.01388 -0.0271 0.0599 1.0000
5.500 0.7357 0.02343 0.01504 -0.0260 0.0581 1.0000
5.750 0.7567 0.02426 0.01596 -0.0248 0.0556 1.0000
6.000 0.7777 0.02566 0.01745 -0.0237 0.0538 1.0000
6.250 0.7977 0.02858 0.02066 -0.0224 0.0527 1.0000
6.500 0.8133 0.03016 0.02261 -0.0199 0.0517 1.0000
6.750 0.8277 0.03172 0.02456 -0.0172 0.0502 1.0000
7.000 0.8386 0.03443 0.02770 -0.0140 0.0499 1.0000
7.250 0.8453 0.03777 0.03143 -0.0103 0.0505 1.0000
7.500 0.8486 0.04142 0.03542 -0.0063 0.0511 1.0000
7.750 0.7658 0.04405 0.03985 0.0087 0.0808 1.0000
8.000 0.7739 0.04673 0.04246 0.0107 0.0791 1.0000
8.500 0.7833 0.06400 0.05993 0.0186 0.0724 1.0000
8.750 0.7701 0.06682 0.06287 0.0229 0.0706 1.0000
9.000 0.7568 0.06951 0.06564 0.0269 0.0693 1.0000
9.250 0.7431 0.07213 0.06831 0.0308 0.0683 1.0000
9.500 0.7256 0.07451 0.07071 0.0352 0.0677 1.0000
9.750 0.7056 0.07700 0.07322 0.0391 0.0672 1.0000
10.000 0.6929 0.07980 0.07603 0.0415 0.0666 1.0000
10.250 0.7292 0.08703 0.08307 0.0398 0.0642 1.0000
10.500 0.7026 0.08959 0.08568 0.0435 0.0642 1.0000
10.750 0.6771 0.09314 0.08929 0.0446 0.0641 1.0000
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Polar data table (+)
Polar graphs
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