NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: NACA 0010-64 (naca001064-il) Reynolds number: 200,000 Max Cl/Cd: 43.35 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001064-il-200000.txt Download as CSV file: xf-naca001064-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-64
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 -0.5347 0.09155 0.08797 -0.0217 1.0000 0.0801
-10.250 -0.5543 0.08443 0.08089 -0.0257 1.0000 0.0823
-9.500 -0.7837 0.06771 0.06368 -0.0302 1.0000 0.0738
-9.250 -0.7746 0.06489 0.06088 -0.0292 1.0000 0.0752
-9.000 -0.8406 0.04812 0.04285 -0.0220 1.0000 0.0474
-8.750 -0.8422 0.04422 0.03862 -0.0187 1.0000 0.0472
-8.500 -0.8409 0.04083 0.03485 -0.0153 1.0000 0.0474
-8.250 -0.8367 0.03757 0.03122 -0.0119 1.0000 0.0475
-8.000 -0.8291 0.03458 0.02784 -0.0088 1.0000 0.0476
-7.750 -0.8181 0.03238 0.02525 -0.0059 1.0000 0.0481
-7.500 -0.8076 0.02927 0.02177 -0.0033 1.0000 0.0495
-7.250 -0.7911 0.02740 0.01981 -0.0017 1.0000 0.0513
-7.000 -0.7730 0.02595 0.01822 0.0000 1.0000 0.0527
-6.750 -0.7540 0.02458 0.01667 0.0016 1.0000 0.0541
-6.500 -0.7347 0.02353 0.01545 0.0032 1.0000 0.0564
-6.250 -0.7146 0.02255 0.01428 0.0048 1.0000 0.0583
-6.000 -0.6940 0.02168 0.01322 0.0064 1.0000 0.0594
-5.750 -0.6723 0.01988 0.01139 0.0074 1.0000 0.0617
-5.500 -0.6521 0.01908 0.01061 0.0087 1.0000 0.0645
-5.250 -0.6316 0.01837 0.00986 0.0100 1.0000 0.0672
-5.000 -0.6112 0.01768 0.00910 0.0115 1.0000 0.0697
-4.750 -0.5907 0.01712 0.00848 0.0129 1.0000 0.0720
-4.500 -0.5725 0.01616 0.00762 0.0145 1.0000 0.0770
-4.250 -0.5526 0.01567 0.00712 0.0159 1.0000 0.0826
-4.000 -0.5333 0.01499 0.00647 0.0174 1.0000 0.0901
-3.750 -0.5135 0.01436 0.00593 0.0187 1.0000 0.1055
-3.500 -0.4947 0.01341 0.00539 0.0200 1.0000 0.1656
-3.250 -0.4783 0.01203 0.00494 0.0213 1.0000 0.3413
-3.000 -0.4639 0.01070 0.00478 0.0235 1.0000 0.5821
-2.750 -0.4451 0.01029 0.00492 0.0257 1.0000 0.7133
-2.500 -0.4246 0.01026 0.00512 0.0277 1.0000 0.7840
-2.250 -0.4044 0.01039 0.00534 0.0298 1.0000 0.8346
-2.000 -0.3850 0.01065 0.00567 0.0323 1.0000 0.8772
-1.750 -0.3642 0.01102 0.00605 0.0346 1.0000 0.9129
-1.500 -0.3349 0.01144 0.00643 0.0349 1.0000 0.9380
-1.250 -0.2966 0.01183 0.00674 0.0329 0.9997 0.9551
-1.000 -0.2325 0.01248 0.00731 0.0261 1.0000 0.9705
-0.750 -0.1528 0.01300 0.00775 0.0160 1.0000 0.9804
-0.500 -0.0926 0.01318 0.00789 0.0091 1.0000 0.9881
-0.250 -0.0460 0.01326 0.00794 0.0045 1.0000 0.9947
0.000 0.0000 0.01330 0.00798 0.0000 1.0000 1.0000
0.250 0.0460 0.01326 0.00794 -0.0045 0.9947 1.0000
0.500 0.0926 0.01318 0.00789 -0.0091 0.9881 1.0000
0.750 0.1527 0.01300 0.00774 -0.0159 0.9804 1.0000
1.000 0.2324 0.01248 0.00731 -0.0261 0.9705 1.0000
1.250 0.2966 0.01183 0.00674 -0.0329 0.9552 0.9997
1.500 0.3348 0.01144 0.00643 -0.0349 0.9379 1.0000
1.750 0.3640 0.01102 0.00605 -0.0346 0.9131 1.0000
2.000 0.3849 0.01065 0.00566 -0.0323 0.8771 1.0000
2.250 0.4043 0.01038 0.00534 -0.0298 0.8348 1.0000
2.500 0.4244 0.01026 0.00511 -0.0277 0.7839 1.0000
2.750 0.4450 0.01029 0.00492 -0.0257 0.7135 1.0000
3.000 0.4638 0.01070 0.00478 -0.0234 0.5822 1.0000
3.250 0.4782 0.01203 0.00494 -0.0213 0.3419 1.0000
3.500 0.4946 0.01341 0.00538 -0.0200 0.1656 1.0000
3.750 0.5134 0.01435 0.00593 -0.0187 0.1056 1.0000
4.000 0.5333 0.01498 0.00647 -0.0174 0.0901 1.0000
4.250 0.5525 0.01567 0.00712 -0.0159 0.0826 1.0000
4.500 0.5724 0.01616 0.00762 -0.0145 0.0770 1.0000
4.750 0.5906 0.01712 0.00848 -0.0129 0.0720 1.0000
5.000 0.6111 0.01768 0.00910 -0.0114 0.0697 1.0000
5.250 0.6315 0.01837 0.00986 -0.0100 0.0672 1.0000
5.500 0.6520 0.01908 0.01061 -0.0086 0.0645 1.0000
5.750 0.6722 0.01988 0.01138 -0.0073 0.0617 1.0000
6.000 0.6939 0.02168 0.01322 -0.0063 0.0594 1.0000
6.250 0.7145 0.02255 0.01428 -0.0048 0.0583 1.0000
6.500 0.7346 0.02353 0.01545 -0.0032 0.0564 1.0000
6.750 0.7539 0.02457 0.01667 -0.0016 0.0541 1.0000
7.000 0.7729 0.02595 0.01822 0.0000 0.0527 1.0000
7.250 0.7910 0.02739 0.01980 0.0017 0.0513 1.0000
7.500 0.8075 0.02926 0.02177 0.0033 0.0495 1.0000
7.750 0.8181 0.03237 0.02525 0.0059 0.0481 1.0000
8.000 0.8290 0.03457 0.02783 0.0088 0.0476 1.0000
8.250 0.8366 0.03757 0.03121 0.0119 0.0475 1.0000
8.500 0.8409 0.04083 0.03485 0.0153 0.0474 1.0000
8.750 0.8422 0.04422 0.03863 0.0187 0.0472 1.0000
9.000 0.8406 0.04813 0.04286 0.0220 0.0474 1.0000
9.250 0.6752 0.05704 0.05335 0.0356 0.0817 1.0000
9.500 0.6452 0.06151 0.05790 0.0373 0.0817 1.0000
9.750 0.6162 0.06722 0.06367 0.0363 0.0823 1.0000
10.000 0.5869 0.07459 0.07108 0.0326 0.0829 1.0000
10.250 0.5542 0.08429 0.08075 0.0257 0.0824 1.0000
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Polar data table (+)
Polar graphs
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