UAG 88-143/20 (uag8814320-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: UAG 88-143/20 (uag8814320-il) Reynolds number: 200,000 Max Cl/Cd: 53.18 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-uag8814320-il-200000-n5.txt Download as CSV file: xf-uag8814320-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: UAG 88-143/20
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
------ -------- --------- --------- -------- -------- --------
-11.250 0.0948 0.09707 0.09222 -0.1530 0.8370 0.0098
-11.000 0.0983 0.09409 0.08925 -0.1539 0.8359 0.0094
-10.750 0.1006 0.09095 0.08612 -0.1548 0.8349 0.0092
-10.500 0.0992 0.08753 0.08275 -0.1553 0.8333 0.0087
-10.250 0.0975 0.08421 0.07949 -0.1557 0.8317 0.0086
-10.000 0.0931 0.08021 0.07553 -0.1562 0.8300 0.0079
-9.750 0.0890 0.07672 0.07210 -0.1567 0.8283 0.0080
-9.500 0.0888 0.07408 0.06950 -0.1571 0.8265 0.0079
-9.250 0.0858 0.07101 0.06646 -0.1576 0.8247 0.0078
-9.000 0.0810 0.06775 0.06323 -0.1583 0.8230 0.0077
-8.750 0.0755 0.06452 0.06004 -0.1591 0.8215 0.0075
-8.500 0.0614 0.06134 0.05697 -0.1591 0.8185 0.0075
-8.250 0.0420 0.05837 0.05408 -0.1589 0.8149 0.0073
-8.000 0.0205 0.05408 0.04982 -0.1591 0.8119 0.0072
-7.750 0.0025 0.04874 0.04436 -0.1593 0.8096 0.0070
-7.500 -0.0532 0.03704 0.03213 -0.1546 0.8047 0.0064
-7.250 -0.0722 0.03138 0.02574 -0.1496 0.8007 0.0062
-7.000 -0.0660 0.02888 0.02278 -0.1469 0.7986 0.0063
-6.750 -0.0518 0.02714 0.02065 -0.1451 0.7969 0.0063
-6.500 -0.0332 0.02577 0.01896 -0.1438 0.7957 0.0064
-6.250 -0.0121 0.02462 0.01751 -0.1429 0.7947 0.0065
-6.000 -0.0110 0.02455 0.01736 -0.1384 0.7894 0.0066
-5.750 0.0056 0.02392 0.01651 -0.1366 0.7868 0.0067
-5.500 0.0263 0.02324 0.01562 -0.1354 0.7849 0.0070
-5.250 0.0496 0.02265 0.01485 -0.1347 0.7836 0.0072
-5.000 0.0741 0.02205 0.01408 -0.1342 0.7825 0.0078
-4.750 0.0999 0.02153 0.01342 -0.1339 0.7816 0.0083
-4.500 0.0947 0.02194 0.01383 -0.1281 0.7746 0.0089
-4.250 0.1148 0.02169 0.01347 -0.1268 0.7724 0.0101
-4.000 0.1380 0.02125 0.01300 -0.1261 0.7709 0.0166
-3.750 0.1641 0.02093 0.01266 -0.1259 0.7697 0.0244
-3.500 0.1922 0.02066 0.01232 -0.1259 0.7688 0.0328
-3.250 0.2210 0.02044 0.01203 -0.1262 0.7680 0.0406
-3.000 0.2030 0.02134 0.01297 -0.1182 0.7586 0.0431
-2.750 0.2295 0.02118 0.01280 -0.1181 0.7573 0.0526
-2.500 0.2575 0.02099 0.01261 -0.1183 0.7563 0.0634
-2.250 0.2384 0.02181 0.01343 -0.1100 0.7473 0.0643
-2.000 0.2618 0.02168 0.01321 -0.1093 0.7453 0.0682
-1.750 0.2885 0.02141 0.01293 -0.1091 0.7441 0.0738
-1.500 0.3174 0.02115 0.01260 -0.1094 0.7431 0.0815
0.000 0.6097 0.01816 0.01200 -0.1365 0.7416 1.0000
0.500 0.5465 0.02044 0.01425 -0.1156 0.7200 1.0000
0.750 0.5715 0.02034 0.01405 -0.1150 0.7183 1.0000
1.000 0.5991 0.02013 0.01375 -0.1149 0.7171 1.0000
1.250 0.6277 0.01988 0.01342 -0.1150 0.7162 1.0000
1.500 0.6573 0.01959 0.01305 -0.1152 0.7154 1.0000
2.000 0.6726 0.02065 0.01402 -0.1089 0.7033 1.0000
2.250 0.6929 0.02074 0.01407 -0.1077 0.7002 1.0000
2.750 0.7250 0.02128 0.01455 -0.1042 0.6906 1.0000
3.000 0.7548 0.02096 0.01419 -0.1044 0.6895 1.0000
3.250 0.7861 0.02057 0.01378 -0.1049 0.6885 1.0000
3.750 0.8131 0.02141 0.01460 -0.1008 0.6764 1.0000
4.000 0.8448 0.02099 0.01417 -0.1013 0.6752 1.0000
4.500 0.8757 0.02172 0.01492 -0.0979 0.6631 1.0000
4.750 0.9082 0.02126 0.01446 -0.0985 0.6615 1.0000
5.250 0.9431 0.02181 0.01507 -0.0957 0.6490 1.0000
5.500 0.9757 0.02134 0.01461 -0.0964 0.6467 1.0000
5.750 0.9821 0.02219 0.01551 -0.0936 0.6365 1.0000
6.000 1.0166 0.02161 0.01495 -0.0945 0.6339 1.0000
6.250 1.0251 0.02239 0.01577 -0.0920 0.6237 1.0000
6.500 1.0595 0.02182 0.01524 -0.0928 0.6202 1.0000
6.750 1.0715 0.02242 0.01589 -0.0908 0.6101 1.0000
7.000 1.1062 0.02184 0.01534 -0.0918 0.6057 1.0000
7.250 1.1194 0.02240 0.01595 -0.0899 0.5952 1.0000
7.500 1.1413 0.02250 0.01611 -0.0892 0.5863 1.0000
7.750 1.1696 0.02225 0.01589 -0.0893 0.5780 1.0000
8.000 1.1861 0.02264 0.01632 -0.0879 0.5664 1.0000
8.250 1.2055 0.02288 0.01659 -0.0868 0.5545 1.0000
8.500 1.2251 0.02310 0.01684 -0.0858 0.5418 1.0000
8.750 1.2438 0.02339 0.01717 -0.0846 0.5286 1.0000
9.000 1.2607 0.02377 0.01756 -0.0833 0.5138 1.0000
9.250 1.2752 0.02425 0.01801 -0.0816 0.4953 1.0000
9.500 1.2855 0.02497 0.01868 -0.0794 0.4743 1.0000
9.750 1.2842 0.02622 0.01970 -0.0757 0.4367 1.0000
10.000 1.2821 0.02769 0.02099 -0.0722 0.4033 1.0000
10.250 1.2775 0.02941 0.02252 -0.0686 0.3680 1.0000
10.500 1.2727 0.03129 0.02421 -0.0652 0.3343 1.0000
10.750 1.2642 0.03354 0.02623 -0.0616 0.2947 1.0000
11.000 1.2578 0.03580 0.02831 -0.0584 0.2576 1.0000
11.250 1.2523 0.03811 0.03043 -0.0556 0.2222 1.0000
11.500 1.2389 0.04115 0.03310 -0.0523 0.1703 1.0000
11.750 1.2256 0.04432 0.03589 -0.0492 0.1173 1.0000
12.250 1.2093 0.05018 0.04125 -0.0444 0.0420 1.0000
12.500 1.1967 0.05371 0.04452 -0.0420 0.0114 1.0000
12.750 1.1977 0.05611 0.04699 -0.0405 0.0085 1.0000
13.000 1.2027 0.05816 0.04913 -0.0394 0.0077 1.0000
13.250 1.2068 0.06033 0.05146 -0.0383 0.0071 1.0000
13.500 1.2090 0.06270 0.05394 -0.0373 0.0057 1.0000
13.750 1.2114 0.06514 0.05652 -0.0364 0.0055 1.0000
14.000 1.2105 0.06799 0.05952 -0.0353 0.0047 1.0000
14.250 1.2124 0.07060 0.06229 -0.0346 0.0046 1.0000
14.500 1.2128 0.07343 0.06528 -0.0339 0.0045 1.0000
14.750 1.2126 0.07635 0.06834 -0.0333 0.0042 1.0000
15.000 1.2111 0.07951 0.07164 -0.0328 0.0040 1.0000
15.250 1.2112 0.08254 0.07480 -0.0325 0.0041 1.0000
15.500 1.2070 0.08615 0.07855 -0.0322 0.0038 1.0000
15.750 1.2055 0.08948 0.08200 -0.0321 0.0038 1.0000
16.000 1.2027 0.09301 0.08565 -0.0321 0.0037 1.0000
16.250 1.1991 0.09667 0.08943 -0.0322 0.0036 1.0000
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