NASA/AMES A-01 AIRFOIL (ames01-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/AMES A-01 AIRFOIL (ames01-il) Reynolds number: 200,000 Max Cl/Cd: 53.31 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ames01-il-200000.txt Download as CSV file: xf-ames01-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/AMES A-01 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6143 0.10553 0.10222 -0.0032 1.0000 0.0546
-9.750 -0.6245 0.09775 0.09443 -0.0124 1.0000 0.0547
-9.500 -0.6400 0.09207 0.08867 -0.0175 1.0000 0.0548
-9.250 -0.6247 0.08660 0.08336 -0.0130 1.0000 0.0564
-9.000 -0.6055 0.08717 0.08395 -0.0067 1.0000 0.0583
-8.750 -0.6083 0.08174 0.07854 -0.0119 1.0000 0.0595
-8.500 -0.6165 0.07629 0.07304 -0.0163 1.0000 0.0606
-8.250 -0.6209 0.07100 0.06766 -0.0198 1.0000 0.0625
-8.000 -0.6364 0.06551 0.06161 -0.0241 1.0000 0.0672
-7.750 -0.5811 0.04616 0.04249 -0.0297 1.0000 0.0698
-7.500 -0.5703 0.04304 0.03940 -0.0290 1.0000 0.0712
-7.250 -0.5665 0.04020 0.03652 -0.0273 1.0000 0.0728
-7.000 -0.5690 0.03769 0.03392 -0.0244 1.0000 0.0748
-6.750 -0.5739 0.03538 0.03138 -0.0209 1.0000 0.0788
-6.500 -0.5995 0.04377 0.03886 -0.0185 1.0000 0.0844
-6.250 -0.5893 0.04171 0.03685 -0.0165 1.0000 0.0865
-6.000 -0.5870 0.03259 0.02627 -0.0100 1.0000 0.0538
-5.750 -0.5750 0.02971 0.02310 -0.0077 1.0000 0.0533
-5.500 -0.5591 0.02860 0.02165 -0.0054 1.0000 0.0544
-5.250 -0.5433 0.02635 0.01905 -0.0035 1.0000 0.0553
-5.000 -0.5245 0.02392 0.01636 -0.0021 1.0000 0.0560
-4.750 -0.5003 0.02215 0.01447 -0.0017 0.9993 0.0575
-4.500 -0.4659 0.02109 0.01333 -0.0034 0.9966 0.0605
-4.250 -0.4302 0.02015 0.01224 -0.0050 0.9941 0.0640
-4.000 -0.3957 0.01924 0.01117 -0.0062 0.9909 0.0664
-3.750 -0.3609 0.01798 0.00983 -0.0077 0.9881 0.0703
-3.500 -0.3239 0.01716 0.00905 -0.0098 0.9855 0.0749
-3.250 -0.2861 0.01650 0.00837 -0.0118 0.9810 0.0796
-3.000 -0.2428 0.01559 0.00751 -0.0150 0.9758 0.0867
-2.750 -0.1934 0.01493 0.00687 -0.0193 0.9706 0.0955
-2.500 -0.1517 0.01423 0.00626 -0.0221 0.9638 0.1086
-2.250 -0.1121 0.01357 0.00573 -0.0244 0.9575 0.1336
-2.000 -0.0965 0.01122 0.00542 -0.0227 0.9489 0.5757
-1.750 -0.0769 0.01054 0.00570 -0.0193 0.9403 0.8133
-1.500 -0.0395 0.01067 0.00593 -0.0193 0.9325 0.8993
-1.250 -0.0009 0.01093 0.00615 -0.0198 0.9217 0.9442
-1.000 0.0524 0.01123 0.00635 -0.0235 0.9141 0.9721
-0.750 0.1157 0.01137 0.00640 -0.0299 0.9072 0.9926
-0.500 0.1535 0.01126 0.00622 -0.0317 0.8966 1.0000
-0.250 0.1710 0.01108 0.00597 -0.0295 0.8848 1.0000
0.000 0.1888 0.01088 0.00570 -0.0271 0.8733 1.0000
0.250 0.2096 0.01069 0.00545 -0.0255 0.8601 1.0000
0.500 0.2302 0.01048 0.00520 -0.0237 0.8461 1.0000
0.750 0.2507 0.01026 0.00492 -0.0218 0.8306 1.0000
1.000 0.2715 0.01005 0.00464 -0.0199 0.8132 1.0000
1.250 0.2939 0.00987 0.00441 -0.0184 0.7909 1.0000
1.500 0.3161 0.00969 0.00416 -0.0167 0.7617 1.0000
1.750 0.3379 0.00956 0.00386 -0.0149 0.7133 1.0000
2.000 0.3589 0.00971 0.00351 -0.0127 0.6077 1.0000
2.250 0.3818 0.01063 0.00352 -0.0120 0.4461 1.0000
2.500 0.4065 0.01129 0.00373 -0.0118 0.3807 1.0000
2.750 0.4314 0.01175 0.00394 -0.0115 0.3524 1.0000
3.000 0.4564 0.01212 0.00416 -0.0111 0.3346 1.0000
3.250 0.4813 0.01250 0.00439 -0.0107 0.3219 1.0000
3.500 0.5062 0.01284 0.00465 -0.0102 0.3113 1.0000
3.750 0.5313 0.01315 0.00491 -0.0098 0.3018 1.0000
4.000 0.5560 0.01358 0.00520 -0.0093 0.2936 1.0000
4.250 0.5814 0.01384 0.00549 -0.0089 0.2858 1.0000
4.500 0.6063 0.01426 0.00582 -0.0084 0.2794 1.0000
4.750 0.6317 0.01459 0.00617 -0.0080 0.2727 1.0000
5.000 0.6568 0.01494 0.00650 -0.0075 0.2661 1.0000
5.250 0.6819 0.01540 0.00693 -0.0071 0.2604 1.0000
5.500 0.7073 0.01572 0.00730 -0.0067 0.2542 1.0000
5.750 0.7324 0.01622 0.00772 -0.0063 0.2484 1.0000
6.000 0.7578 0.01657 0.00817 -0.0059 0.2424 1.0000
6.250 0.7832 0.01693 0.00854 -0.0055 0.2363 1.0000
6.500 0.8084 0.01748 0.00906 -0.0052 0.2307 1.0000
6.750 0.8338 0.01777 0.00949 -0.0048 0.2241 1.0000
7.000 0.8590 0.01823 0.00988 -0.0045 0.2180 1.0000
7.250 0.8840 0.01856 0.01036 -0.0042 0.2111 1.0000
7.500 0.9090 0.01887 0.01068 -0.0038 0.2045 1.0000
7.750 0.9337 0.01929 0.01120 -0.0035 0.1978 1.0000
8.000 0.9583 0.01947 0.01143 -0.0031 0.1902 1.0000
8.250 0.9824 0.01975 0.01181 -0.0027 0.1824 1.0000
8.500 1.0064 0.01985 0.01195 -0.0023 0.1742 1.0000
8.750 1.0302 0.02004 0.01228 -0.0018 0.1650 1.0000
9.000 1.0535 0.02023 0.01251 -0.0013 0.1561 1.0000
9.250 1.0765 0.02039 0.01272 -0.0008 0.1456 1.0000
9.500 1.0992 0.02062 0.01307 -0.0002 0.1330 1.0000
9.750 1.1205 0.02107 0.01352 0.0004 0.1184 1.0000
10.000 1.1414 0.02168 0.01420 0.0011 0.1011 1.0000
10.250 1.1593 0.02264 0.01511 0.0021 0.0853 1.0000
10.500 1.1749 0.02386 0.01630 0.0034 0.0732 1.0000
10.750 1.1887 0.02521 0.01771 0.0049 0.0647 1.0000
11.000 1.1978 0.02692 0.01934 0.0068 0.0587 1.0000
11.250 1.2124 0.02806 0.02067 0.0082 0.0542 1.0000
11.500 1.2222 0.02945 0.02209 0.0100 0.0505 1.0000
11.750 1.2267 0.03132 0.02400 0.0124 0.0477 1.0000
12.000 1.2340 0.03269 0.02555 0.0144 0.0455 1.0000
12.250 1.2399 0.03428 0.02726 0.0164 0.0436 1.0000
12.500 1.2450 0.03599 0.02907 0.0181 0.0419 1.0000
12.750 1.2485 0.03801 0.03114 0.0197 0.0404 1.0000
13.000 1.2499 0.04095 0.03414 0.0213 0.0388 1.0000
13.250 1.2516 0.04299 0.03641 0.0225 0.0380 1.0000
13.500 1.2516 0.04536 0.03899 0.0235 0.0371 1.0000
13.750 1.2502 0.04803 0.04184 0.0242 0.0361 1.0000
14.000 1.2468 0.05103 0.04503 0.0245 0.0354 1.0000
14.250 1.2417 0.05441 0.04859 0.0244 0.0347 1.0000
14.500 1.2349 0.05815 0.05252 0.0238 0.0342 1.0000
14.750 1.2264 0.06233 0.05687 0.0227 0.0338 1.0000
15.000 1.2159 0.06701 0.06173 0.0210 0.0334 1.0000
15.250 1.2032 0.07233 0.06723 0.0185 0.0332 1.0000
15.500 1.1871 0.07849 0.07359 0.0153 0.0331 1.0000
15.750 1.1671 0.08577 0.08108 0.0111 0.0330 1.0000
16.000 1.1396 0.09503 0.09059 0.0052 0.0332 1.0000
16.250 1.0973 0.10809 0.10394 -0.0033 0.0339 1.0000
16.500 0.9043 0.16200 0.15823 -0.0349 0.0395 1.0000
16.750 0.8526 0.18894 0.18505 -0.0463 0.0476 1.0000
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