NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il) Reynolds number: 200,000 Max Cl/Cd: 53.29 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ames03-il-200000-n5.txt Download as CSV file: xf-ames03-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/AMES A-03 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6928 0.10112 0.09800 0.0197 0.9027 0.0160
-10.000 -0.7005 0.09432 0.09122 0.0155 0.9001 0.0160
-9.750 -0.7169 0.08363 0.08054 0.0075 0.8974 0.0159
-9.250 -0.7545 0.06596 0.06259 -0.0065 0.8904 0.0156
-9.000 -0.7776 0.05710 0.05334 -0.0085 0.8870 0.0157
-8.750 -0.7944 0.04895 0.04460 -0.0085 0.8841 0.0159
-8.500 -0.7893 0.04550 0.04087 -0.0078 0.8818 0.0162
-8.250 -0.7773 0.04210 0.03716 -0.0078 0.8791 0.0165
-8.000 -0.7639 0.03838 0.03302 -0.0075 0.8765 0.0168
-7.750 -0.7471 0.03532 0.02957 -0.0071 0.8741 0.0171
-7.500 -0.7280 0.03265 0.02651 -0.0066 0.8721 0.0175
-7.250 -0.7074 0.03020 0.02365 -0.0061 0.8702 0.0180
-7.000 -0.6855 0.02804 0.02109 -0.0054 0.8685 0.0187
-6.750 -0.6620 0.02619 0.01887 -0.0049 0.8669 0.0195
-6.500 -0.6342 0.02482 0.01713 -0.0051 0.8644 0.0207
-6.250 -0.6079 0.02344 0.01569 -0.0054 0.8621 0.0218
-6.000 -0.5810 0.02242 0.01455 -0.0055 0.8601 0.0227
-5.750 -0.5542 0.02141 0.01341 -0.0054 0.8582 0.0237
-5.500 -0.5276 0.02046 0.01233 -0.0053 0.8565 0.0249
-5.250 -0.5011 0.01967 0.01141 -0.0050 0.8550 0.0263
-5.000 -0.4755 0.01884 0.01056 -0.0048 0.8535 0.0283
-4.750 -0.4486 0.01827 0.00995 -0.0048 0.8519 0.0304
-4.500 -0.4191 0.01762 0.00924 -0.0054 0.8496 0.0327
-4.250 -0.3904 0.01699 0.00856 -0.0058 0.8474 0.0353
-4.000 -0.3619 0.01651 0.00810 -0.0062 0.8456 0.0397
-3.750 -0.3334 0.01610 0.00762 -0.0064 0.8438 0.0444
-3.500 -0.3054 0.01564 0.00717 -0.0066 0.8422 0.0515
-3.250 -0.2775 0.01525 0.00680 -0.0068 0.8406 0.0630
-3.000 -0.2510 0.01486 0.00644 -0.0065 0.8387 0.0816
-2.750 -0.2231 0.01435 0.00613 -0.0068 0.8351 0.1233
-2.500 -0.1952 0.01371 0.00584 -0.0072 0.8304 0.2040
-2.250 -0.1707 0.01274 0.00550 -0.0070 0.8265 0.3589
-2.000 -0.1493 0.01163 0.00530 -0.0058 0.8236 0.5797
-1.750 -0.1249 0.01118 0.00536 -0.0047 0.8196 0.7076
-1.500 -0.0998 0.01104 0.00539 -0.0036 0.8151 0.7746
-1.250 -0.0767 0.01094 0.00536 -0.0018 0.8112 0.8191
-1.000 -0.0557 0.01086 0.00529 0.0005 0.8078 0.8542
-0.750 -0.0316 0.01085 0.00532 0.0020 0.8018 0.8872
-0.500 -0.0105 0.01078 0.00525 0.0044 0.7967 0.9167
-0.250 0.0129 0.01064 0.00507 0.0062 0.7928 0.9358
0.000 0.0437 0.01057 0.00496 0.0057 0.7852 0.9460
0.250 0.0709 0.01036 0.00468 0.0063 0.7784 0.9562
0.500 0.1043 0.01022 0.00450 0.0054 0.7675 0.9635
0.750 0.1361 0.01006 0.00430 0.0048 0.7566 0.9718
1.000 0.1703 0.00991 0.00410 0.0037 0.7441 0.9781
1.250 0.2046 0.00979 0.00395 0.0025 0.7284 0.9849
1.500 0.2400 0.00967 0.00379 0.0010 0.7076 0.9906
1.750 0.2741 0.00954 0.00357 -0.0001 0.6696 0.9966
2.000 0.3013 0.01001 0.00302 0.0002 0.4676 1.0000
2.250 0.3302 0.01079 0.00325 -0.0010 0.3593 1.0000
2.500 0.3571 0.01122 0.00342 -0.0015 0.3152 1.0000
2.750 0.3840 0.01155 0.00358 -0.0018 0.2901 1.0000
3.000 0.4113 0.01185 0.00376 -0.0021 0.2733 1.0000
3.250 0.4388 0.01212 0.00394 -0.0024 0.2612 1.0000
3.500 0.4667 0.01240 0.00417 -0.0028 0.2522 1.0000
3.750 0.4946 0.01268 0.00439 -0.0032 0.2434 1.0000
4.000 0.5226 0.01296 0.00463 -0.0035 0.2358 1.0000
4.250 0.5505 0.01324 0.00490 -0.0039 0.2288 1.0000
4.500 0.5784 0.01355 0.00517 -0.0042 0.2224 1.0000
4.750 0.6064 0.01382 0.00545 -0.0045 0.2157 1.0000
5.000 0.6340 0.01419 0.00577 -0.0048 0.2096 1.0000
5.250 0.6620 0.01443 0.00607 -0.0051 0.2032 1.0000
5.500 0.6896 0.01476 0.00638 -0.0053 0.1971 1.0000
5.750 0.7172 0.01507 0.00672 -0.0056 0.1910 1.0000
6.000 0.7448 0.01535 0.00706 -0.0058 0.1842 1.0000
6.250 0.7721 0.01570 0.00741 -0.0061 0.1781 1.0000
6.500 0.7996 0.01597 0.00777 -0.0063 0.1711 1.0000
6.750 0.8266 0.01633 0.00813 -0.0065 0.1646 1.0000
7.000 0.8539 0.01661 0.00852 -0.0067 0.1570 1.0000
7.250 0.8807 0.01697 0.00889 -0.0069 0.1498 1.0000
7.500 0.9075 0.01729 0.00927 -0.0071 0.1405 1.0000
7.750 0.9340 0.01764 0.00970 -0.0072 0.1306 1.0000
8.000 0.9601 0.01804 0.01012 -0.0074 0.1197 1.0000
8.250 0.9858 0.01850 0.01059 -0.0075 0.1080 1.0000
8.500 1.0109 0.01903 0.01111 -0.0075 0.0959 1.0000
8.750 1.0354 0.01964 0.01174 -0.0075 0.0842 1.0000
9.000 1.0592 0.02035 0.01244 -0.0075 0.0731 1.0000
9.250 1.0824 0.02110 0.01321 -0.0073 0.0627 1.0000
9.500 1.1052 0.02191 0.01407 -0.0072 0.0537 1.0000
9.750 1.1270 0.02281 0.01502 -0.0069 0.0462 1.0000
10.000 1.1474 0.02385 0.01610 -0.0066 0.0398 1.0000
10.250 1.1676 0.02484 0.01718 -0.0062 0.0349 1.0000
10.500 1.1854 0.02605 0.01845 -0.0056 0.0316 1.0000
10.750 1.2032 0.02714 0.01970 -0.0049 0.0290 1.0000
11.000 1.2189 0.02839 0.02104 -0.0042 0.0268 1.0000
11.250 1.2304 0.02993 0.02267 -0.0033 0.0250 1.0000
11.500 1.2424 0.03123 0.02416 -0.0023 0.0236 1.0000
11.750 1.2505 0.03267 0.02575 -0.0008 0.0224 1.0000
12.000 1.2572 0.03430 0.02752 0.0005 0.0215 1.0000
12.250 1.2621 0.03613 0.02947 0.0017 0.0208 1.0000
12.500 1.2641 0.03826 0.03172 0.0028 0.0201 1.0000
12.750 1.2622 0.04082 0.03439 0.0039 0.0196 1.0000
13.000 1.2618 0.04338 0.03711 0.0046 0.0191 1.0000
13.250 1.2615 0.04606 0.03997 0.0051 0.0187 1.0000
13.500 1.2591 0.04907 0.04318 0.0052 0.0183 1.0000
13.750 1.2547 0.05249 0.04678 0.0049 0.0178 1.0000
14.000 1.2482 0.05639 0.05086 0.0041 0.0175 1.0000
14.250 1.2396 0.06090 0.05555 0.0025 0.0171 1.0000
14.500 1.2287 0.06620 0.06106 0.0001 0.0169 1.0000
14.750 1.2159 0.07242 0.06747 -0.0034 0.0167 1.0000
15.000 1.2014 0.07955 0.07478 -0.0077 0.0166 1.0000
15.250 1.1853 0.08726 0.08266 -0.0123 0.0165 1.0000
15.500 1.1679 0.09526 0.09083 -0.0169 0.0165 1.0000
15.750 1.1496 0.10337 0.09907 -0.0214 0.0164 1.0000
16.000 1.1308 0.11155 0.10738 -0.0259 0.0164 1.0000
16.250 1.1119 0.11988 0.11584 -0.0304 0.0164 1.0000
16.500 1.0923 0.12848 0.12458 -0.0352 0.0164 1.0000
16.750 1.0711 0.13794 0.13417 -0.0405 0.0164 1.0000
17.000 1.0442 0.14948 0.14586 -0.0471 0.0166 1.0000
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