AH-6-40-7 AIRFOIL (ah6407-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH-6-40-7 AIRFOIL (ah6407-il) Reynolds number: 200,000 Max Cl/Cd: 85.64 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah6407-il-200000-n5.txt Download as CSV file: xf-ah6407-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH-6-40-7 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3063 0.10528 0.10187 -0.0273 1.0000 0.0233
-8.000 -0.3133 0.10404 0.10069 -0.0257 1.0000 0.0236
-7.750 -0.3210 0.10276 0.09948 -0.0240 0.9996 0.0238
-7.500 -0.3063 0.09920 0.09593 -0.0293 0.9951 0.0240
-7.250 -0.2867 0.09498 0.09171 -0.0354 0.9900 0.0241
-6.750 -0.2535 0.08341 0.08012 -0.0440 0.9822 0.0158
-6.500 -0.2304 0.07901 0.07571 -0.0496 0.9790 0.0155
-6.250 -0.2065 0.07437 0.07105 -0.0563 0.9734 0.0155
-5.500 -0.0993 0.05649 0.05302 -0.0867 0.9613 0.0167
-5.250 -0.0581 0.05076 0.04717 -0.0967 0.9584 0.0170
-5.000 -0.0200 0.04648 0.04279 -0.1041 0.9540 0.0176
-4.750 0.0206 0.04315 0.03935 -0.1108 0.9514 0.0196
-4.500 0.0842 0.03431 0.03014 -0.1255 0.9502 0.0216
-4.250 0.1573 0.02151 0.01593 -0.1412 0.9502 0.0256
-4.000 0.1900 0.02056 0.01483 -0.1429 0.9460 0.0281
-3.750 0.2262 0.01884 0.01266 -0.1451 0.9422 0.0315
-3.500 0.2627 0.01784 0.01123 -0.1469 0.9391 0.0349
-3.250 0.2963 0.01621 0.00932 -0.1485 0.9347 0.0380
-3.000 0.3282 0.01560 0.00859 -0.1494 0.9291 0.0414
-2.750 0.3613 0.01477 0.00755 -0.1503 0.9221 0.0433
-2.500 0.3936 0.01406 0.00668 -0.1509 0.9130 0.0450
-2.250 0.4229 0.01363 0.00612 -0.1508 0.9018 0.0473
-2.000 0.4529 0.01315 0.00553 -0.1510 0.8925 0.0481
-1.750 0.4834 0.01262 0.00494 -0.1513 0.8839 0.0490
-1.500 0.5125 0.01219 0.00447 -0.1514 0.8735 0.0513
-1.250 0.5417 0.01189 0.00411 -0.1515 0.8633 0.0546
-1.000 0.5707 0.01167 0.00382 -0.1515 0.8525 0.0592
-0.750 0.5993 0.01145 0.00358 -0.1514 0.8403 0.0678
-0.500 0.6277 0.01122 0.00344 -0.1513 0.8267 0.1052
-0.250 0.6559 0.01101 0.00341 -0.1513 0.8123 0.1768
0.000 0.6837 0.01089 0.00338 -0.1511 0.7968 0.2314
0.250 0.7112 0.01080 0.00334 -0.1509 0.7806 0.2752
0.500 0.7390 0.01058 0.00338 -0.1508 0.7631 0.3874
0.750 0.7576 0.00944 0.00330 -0.1484 0.7453 1.0000
1.000 0.7849 0.00957 0.00326 -0.1480 0.7248 1.0000
1.250 0.8119 0.00973 0.00325 -0.1476 0.7015 1.0000
1.500 0.8385 0.00992 0.00327 -0.1471 0.6759 1.0000
1.750 0.8647 0.01015 0.00332 -0.1466 0.6481 1.0000
2.000 0.8907 0.01040 0.00340 -0.1461 0.6191 1.0000
2.250 0.9164 0.01070 0.00351 -0.1455 0.5881 1.0000
2.500 0.9416 0.01103 0.00367 -0.1449 0.5551 1.0000
2.750 0.9666 0.01140 0.00386 -0.1443 0.5221 1.0000
3.000 0.9914 0.01179 0.00407 -0.1437 0.4913 1.0000
3.250 1.0163 0.01218 0.00433 -0.1432 0.4651 1.0000
3.500 1.0413 0.01256 0.00460 -0.1426 0.4427 1.0000
3.750 1.0663 0.01294 0.00489 -0.1421 0.4234 1.0000
4.000 1.0915 0.01330 0.00519 -0.1417 0.4062 1.0000
4.250 1.1166 0.01367 0.00553 -0.1412 0.3903 1.0000
4.500 1.1416 0.01404 0.00587 -0.1407 0.3757 1.0000
4.750 1.1665 0.01441 0.00623 -0.1402 0.3630 1.0000
5.000 1.1915 0.01479 0.00662 -0.1397 0.3518 1.0000
5.250 1.2166 0.01514 0.00702 -0.1393 0.3415 1.0000
5.500 1.2411 0.01553 0.00743 -0.1387 0.3302 1.0000
5.750 1.2653 0.01595 0.00786 -0.1381 0.3179 1.0000
6.000 1.2891 0.01637 0.00832 -0.1374 0.3039 1.0000
6.250 1.3122 0.01680 0.00874 -0.1367 0.2830 1.0000
6.500 1.3343 0.01732 0.00919 -0.1358 0.2596 1.0000
6.750 1.3558 0.01789 0.00967 -0.1349 0.2318 1.0000
7.000 1.3768 0.01852 0.01022 -0.1339 0.1978 1.0000
7.250 1.3932 0.01967 0.01103 -0.1323 0.1321 1.0000
7.500 1.4025 0.02173 0.01252 -0.1298 0.0566 1.0000
7.750 1.4150 0.02334 0.01391 -0.1275 0.0242 1.0000
8.000 1.4312 0.02444 0.01508 -0.1256 0.0189 1.0000
8.250 1.4456 0.02566 0.01644 -0.1234 0.0158 1.0000
8.500 1.4609 0.02666 0.01762 -0.1214 0.0142 1.0000
8.750 1.4733 0.02784 0.01898 -0.1190 0.0131 1.0000
9.000 1.4828 0.02913 0.02044 -0.1162 0.0123 1.0000
9.250 1.4880 0.03054 0.02200 -0.1127 0.0116 1.0000
9.500 1.4893 0.03220 0.02386 -0.1089 0.0111 1.0000
9.750 1.4857 0.03436 0.02617 -0.1047 0.0104 1.0000
10.000 1.4857 0.03638 0.02833 -0.1013 0.0100 1.0000
10.250 1.4905 0.03807 0.03018 -0.0987 0.0095 1.0000
10.500 1.4927 0.04008 0.03234 -0.0961 0.0091 1.0000
10.750 1.4932 0.04236 0.03478 -0.0935 0.0088 1.0000
11.000 1.4934 0.04478 0.03735 -0.0911 0.0085 1.0000
11.250 1.4934 0.04734 0.04007 -0.0889 0.0083 1.0000
11.500 1.4929 0.05005 0.04293 -0.0870 0.0081 1.0000
11.750 1.4921 0.05289 0.04593 -0.0852 0.0079 1.0000
12.000 1.4908 0.05589 0.04909 -0.0837 0.0077 1.0000
12.250 1.4887 0.05907 0.05243 -0.0823 0.0076 1.0000
12.500 1.4858 0.06243 0.05596 -0.0812 0.0075 1.0000
12.750 1.4818 0.06602 0.05971 -0.0804 0.0073 1.0000
13.000 1.4769 0.06983 0.06368 -0.0798 0.0072 1.0000
13.250 1.4706 0.07389 0.06789 -0.0795 0.0071 1.0000
13.500 1.4626 0.07838 0.07253 -0.0793 0.0069 1.0000
13.750 1.4523 0.08338 0.07772 -0.0796 0.0068 1.0000
14.000 1.4424 0.08850 0.08309 -0.0809 0.0067 1.0000
14.250 1.4317 0.09403 0.08892 -0.0827 0.0066 1.0000
14.500 1.4203 0.09998 0.09511 -0.0849 0.0065 1.0000
14.750 1.4083 0.10634 0.10170 -0.0877 0.0064 1.0000
15.000 1.3958 0.11299 0.10856 -0.0909 0.0064 1.0000
15.250 1.3831 0.12001 0.11579 -0.0945 0.0064 1.0000
15.500 1.3700 0.12741 0.12339 -0.0987 0.0063 1.0000
15.750 1.3572 0.13505 0.13122 -0.1032 0.0063 1.0000
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Polar data table (+)
Polar graphs
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