DOUGLAS LA203A AIRFOIL (la203a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: DOUGLAS LA203A AIRFOIL (la203a-il) Reynolds number: 200,000 Max Cl/Cd: 82.36 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-la203a-il-200000.txt Download as CSV file: xf-la203a-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: DOUGLAS LA203A 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0291 0.10144 0.09694 -0.0971 0.8436 0.0618
-9.500 -0.0216 0.09881 0.09431 -0.0985 0.8382 0.0633
-9.250 -0.0451 0.09458 0.09006 -0.1086 0.8325 0.0661
-9.000 -0.0258 0.09179 0.08724 -0.1062 0.8286 0.0665
-8.750 -0.0090 0.08963 0.08509 -0.1050 0.8238 0.0672
-8.500 0.0038 0.08742 0.08288 -0.1051 0.8192 0.0681
-8.250 0.0137 0.08503 0.08047 -0.1061 0.8149 0.0694
-8.000 0.0212 0.08240 0.07779 -0.1078 0.8111 0.0712
-7.750 -0.0029 0.07522 0.07070 -0.1222 0.8051 0.0743
-7.500 0.0173 0.07385 0.06932 -0.1183 0.8011 0.0749
-7.250 0.0333 0.07215 0.06761 -0.1169 0.7972 0.0756
-7.000 0.0464 0.07011 0.06554 -0.1172 0.7938 0.0768
-6.750 0.0556 0.06760 0.06304 -0.1190 0.7900 0.0786
-6.500 0.0404 0.05693 0.05215 -0.1432 0.7839 0.0837
-6.250 0.0588 0.05530 0.05061 -0.1413 0.7801 0.0845
-6.000 0.0766 0.05364 0.04894 -0.1410 0.7767 0.0857
-5.750 0.0938 0.05144 0.04666 -0.1430 0.7734 0.0883
-5.500 0.1069 0.04645 0.04134 -0.1510 0.7687 0.0947
-5.250 0.1265 0.04488 0.03983 -0.1508 0.7648 0.0964
-5.000 0.1509 0.04196 0.03639 -0.1561 0.7611 0.1054
-4.750 0.1734 0.03987 0.03436 -0.1562 0.7583 0.1070
-4.500 0.1946 0.03848 0.03299 -0.1565 0.7542 0.1100
-4.250 0.2202 0.03644 0.03066 -0.1591 0.7500 0.1196
-4.000 0.2446 0.03496 0.02920 -0.1594 0.7465 0.1230
-3.750 0.2909 0.02838 0.02116 -0.1644 0.7438 0.0839
-3.500 0.3192 0.02675 0.01946 -0.1649 0.7408 0.0805
-3.250 0.3499 0.02499 0.01711 -0.1654 0.7362 0.0739
-3.000 0.3783 0.02378 0.01578 -0.1658 0.7326 0.0736
-2.750 0.4087 0.02282 0.01464 -0.1662 0.7295 0.0737
-2.500 0.4401 0.02209 0.01370 -0.1667 0.7270 0.0742
-2.250 0.4643 0.02134 0.01307 -0.1665 0.7223 0.0761
-2.000 0.4917 0.02092 0.01268 -0.1665 0.7184 0.0784
-1.750 0.5216 0.02040 0.01208 -0.1667 0.7153 0.0803
-1.500 0.5527 0.01992 0.01150 -0.1670 0.7128 0.0822
-1.250 0.5789 0.01955 0.01120 -0.1669 0.7087 0.0844
-1.000 0.6061 0.01929 0.01105 -0.1670 0.7044 0.0884
-0.750 0.6364 0.01904 0.01076 -0.1674 0.7010 0.0931
-0.500 0.6695 0.01851 0.01031 -0.1685 0.6983 0.0993
-0.250 0.7011 0.01830 0.01015 -0.1695 0.6951 0.1079
0.000 0.7295 0.01825 0.01024 -0.1700 0.6900 0.1240
0.250 0.7741 0.01691 0.01056 -0.1745 0.6863 0.6433
0.500 0.7997 0.01711 0.01080 -0.1732 0.6832 0.7035
0.750 0.8259 0.01735 0.01099 -0.1720 0.6807 0.7360
1.000 0.8438 0.01781 0.01159 -0.1700 0.6749 0.7581
1.250 0.8635 0.01803 0.01186 -0.1677 0.6706 0.7796
1.500 0.8852 0.01812 0.01195 -0.1657 0.6674 0.7993
1.750 0.9091 0.01819 0.01196 -0.1641 0.6648 0.8166
2.000 0.9279 0.01856 0.01242 -0.1625 0.6593 0.8299
2.250 0.9496 0.01866 0.01255 -0.1611 0.6547 0.8384
2.500 0.9795 0.01865 0.01249 -0.1614 0.6514 0.8477
2.750 1.0064 0.01856 0.01235 -0.1608 0.6487 0.8556
3.000 1.0303 0.01884 0.01267 -0.1604 0.6438 0.8645
3.250 1.0526 0.01900 0.01288 -0.1595 0.6386 0.8714
3.500 1.0806 0.01899 0.01285 -0.1594 0.6350 0.8790
3.750 1.1100 0.01889 0.01271 -0.1595 0.6321 0.8868
4.000 1.1344 0.01900 0.01284 -0.1589 0.6282 0.8962
4.250 1.1519 0.01927 0.01322 -0.1572 0.6221 0.9062
4.500 1.1779 0.01925 0.01319 -0.1568 0.6182 0.9168
4.750 1.2035 0.01909 0.01301 -0.1561 0.6151 0.9296
5.000 1.2249 0.01901 0.01293 -0.1546 0.6117 0.9462
5.250 1.2370 0.01925 0.01332 -0.1521 0.6050 0.9810
5.500 1.2745 0.01928 0.01334 -0.1543 0.6006 0.9999
5.750 1.3148 0.01920 0.01320 -0.1569 0.5972 0.9999
6.000 1.3461 0.01955 0.01360 -0.1582 0.5916 0.9999
6.250 1.3764 0.01980 0.01389 -0.1592 0.5854 0.9999
6.500 1.4132 0.01963 0.01368 -0.1608 0.5808 0.9999
6.750 1.4441 0.01974 0.01379 -0.1616 0.5749 0.9999
7.000 1.4704 0.01985 0.01395 -0.1616 0.5671 0.9999
7.250 1.5083 0.01941 0.01337 -0.1631 0.5609 0.9999
7.500 1.5268 0.01965 0.01373 -0.1617 0.5508 0.9999
7.750 1.5598 0.01930 0.01326 -0.1624 0.5426 0.9999
8.000 1.5774 0.01952 0.01359 -0.1608 0.5320 0.9999
8.250 1.6030 0.01952 0.01356 -0.1604 0.5229 0.9999
8.500 1.6221 0.01974 0.01382 -0.1590 0.5128 0.9999
8.750 1.6420 0.01998 0.01408 -0.1577 0.5030 0.9999
9.000 1.6621 0.02018 0.01428 -0.1564 0.4929 0.9999
9.250 1.6745 0.02065 0.01484 -0.1541 0.4820 0.9999
9.500 1.6897 0.02098 0.01514 -0.1520 0.4714 0.9999
9.750 1.6985 0.02156 0.01576 -0.1491 0.4596 0.9999
10.000 1.7058 0.02229 0.01654 -0.1463 0.4474 0.9999
10.250 1.7133 0.02309 0.01734 -0.1435 0.4349 0.9999
10.500 1.7186 0.02408 0.01831 -0.1407 0.4211 0.9999
10.750 1.7205 0.02539 0.01963 -0.1378 0.4061 0.9999
11.000 1.7208 0.02695 0.02120 -0.1351 0.3900 0.9999
11.250 1.7194 0.02877 0.02302 -0.1324 0.3724 0.9999
11.500 1.7154 0.03092 0.02511 -0.1297 0.3532 0.9999
11.750 1.7093 0.03338 0.02755 -0.1272 0.3316 0.9999
12.000 1.6994 0.03624 0.03034 -0.1245 0.3080 0.9999
12.250 1.6860 0.03951 0.03349 -0.1219 0.2837 0.9999
12.500 1.6707 0.04310 0.03697 -0.1193 0.2586 0.9999
12.750 1.6536 0.04704 0.04078 -0.1170 0.2356 0.9999
13.000 1.6386 0.05100 0.04463 -0.1150 0.2128 0.9999
13.250 1.6228 0.05520 0.04872 -0.1132 0.1920 0.9999
13.750 1.5951 0.06364 0.05698 -0.1104 0.1562 0.9999
14.000 1.5833 0.06781 0.06107 -0.1093 0.1413 0.9999
14.250 1.5722 0.07199 0.06518 -0.1084 0.1291 0.9999
14.500 1.5639 0.07591 0.06907 -0.1076 0.1184 0.9999
14.750 1.5584 0.07956 0.07270 -0.1070 0.1092 0.9999
15.000 1.5515 0.08340 0.07651 -0.1064 0.1021 0.9999
15.250 1.5475 0.08693 0.08003 -0.1059 0.0955 0.9999
15.500 1.5443 0.09034 0.08344 -0.1055 0.0902 0.9999
15.750 1.5429 0.09358 0.08671 -0.1052 0.0853 0.9999
16.000 1.5408 0.09681 0.08990 -0.1048 0.0813 0.9999
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