AH 85-L-120/17 (ah85l120-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AH 85-L-120/17 (ah85l120-il) Reynolds number: 1,000,000 Max Cl/Cd: 55.39 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah85l120-il-1000000.txt Download as CSV file: xf-ah85l120-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AH 85-L-120/17
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7329 0.07178 0.07011 -0.0404 0.9523 0.0070
-12.000 -0.9171 0.03812 0.03497 -0.0494 0.9359 0.0056
-11.750 -0.9101 0.03542 0.03203 -0.0504 0.9301 0.0057
-11.250 -0.8779 0.03373 0.03018 -0.0517 0.9206 0.0061
-11.000 -0.8571 0.03347 0.02988 -0.0525 0.9168 0.0064
-10.750 -0.8600 0.02942 0.02541 -0.0504 0.9125 0.0066
-10.500 -0.8443 0.02881 0.02473 -0.0496 0.9092 0.0068
-10.250 -0.8374 0.02576 0.02132 -0.0476 0.9059 0.0068
-10.000 -0.8211 0.02470 0.02010 -0.0465 0.9030 0.0074
-9.750 -0.8043 0.02320 0.01841 -0.0456 0.9003 0.0073
-9.500 -0.7886 0.02259 0.01767 -0.0439 0.8976 0.0078
-9.250 -0.7711 0.02332 0.01836 -0.0422 0.8949 0.0082
-9.000 -0.7517 0.02061 0.01541 -0.0416 0.8931 0.0081
-8.750 -0.7269 0.01778 0.01231 -0.0421 0.8918 0.0088
-8.500 -0.7061 0.01670 0.01113 -0.0413 0.8898 0.0090
-8.250 -0.6872 0.01557 0.00990 -0.0402 0.8875 0.0092
-8.000 -0.6683 0.01510 0.00938 -0.0390 0.8855 0.0095
-7.750 -0.6480 0.01492 0.00921 -0.0379 0.8836 0.0105
-7.500 -0.6317 0.01418 0.00839 -0.0360 0.8814 0.0105
-7.250 -0.6156 0.01356 0.00769 -0.0340 0.8792 0.0108
-7.000 -0.5959 0.01318 0.00726 -0.0327 0.8772 0.0116
-6.750 -0.5753 0.01284 0.00687 -0.0316 0.8753 0.0121
-6.500 -0.5532 0.01260 0.00660 -0.0307 0.8734 0.0125
-6.250 -0.5398 0.01183 0.00572 -0.0281 0.8714 0.0131
-6.000 -0.5227 0.01128 0.00509 -0.0262 0.8693 0.0142
-5.750 -0.5020 0.01096 0.00476 -0.0250 0.8674 0.0158
-5.500 -0.4805 0.01067 0.00444 -0.0239 0.8655 0.0177
-5.250 -0.4597 0.01032 0.00405 -0.0227 0.8635 0.0229
-5.000 -0.4373 0.01008 0.00380 -0.0218 0.8618 0.0273
-4.750 -0.4184 0.00964 0.00350 -0.0203 0.8598 0.0593
-4.500 -0.4014 0.00914 0.00325 -0.0185 0.8578 0.1173
-4.250 -0.3855 0.00856 0.00299 -0.0164 0.8557 0.1901
-4.000 -0.3707 0.00795 0.00274 -0.0142 0.8532 0.2787
-3.750 -0.3554 0.00737 0.00250 -0.0121 0.8508 0.3675
-3.500 -0.3476 0.00650 0.00221 -0.0084 0.8483 0.5140
-3.250 -0.3324 0.00603 0.00203 -0.0059 0.8461 0.5982
-3.000 -0.3142 0.00574 0.00196 -0.0040 0.8438 0.6594
-2.750 -0.2950 0.00553 0.00196 -0.0021 0.8414 0.7179
-2.500 -0.2712 0.00550 0.00199 -0.0012 0.8389 0.7473
-2.250 -0.2449 0.00550 0.00197 -0.0009 0.8366 0.7601
-2.000 -0.2182 0.00553 0.00199 -0.0007 0.8346 0.7711
-1.750 -0.1907 0.00555 0.00200 -0.0006 0.8328 0.7780
-1.500 -0.1636 0.00562 0.00203 -0.0005 0.8308 0.7852
-1.250 -0.1370 0.00565 0.00208 -0.0003 0.8286 0.7919
-1.000 -0.1101 0.00569 0.00212 -0.0001 0.8260 0.7977
-0.750 -0.0834 0.00572 0.00214 0.0001 0.8234 0.8036
-0.500 -0.0551 0.00577 0.00220 0.0000 0.8209 0.8085
-0.250 -0.0272 0.00580 0.00221 -0.0001 0.8185 0.8126
0.000 0.0000 0.00584 0.00222 0.0000 0.8158 0.8159
0.250 0.0272 0.00579 0.00221 0.0001 0.8124 0.8186
0.500 0.0552 0.00576 0.00219 0.0000 0.8083 0.8209
0.750 0.0834 0.00572 0.00213 -0.0001 0.8034 0.8234
1.000 0.1102 0.00569 0.00212 0.0001 0.7978 0.8260
1.250 0.1370 0.00565 0.00207 0.0003 0.7918 0.8286
1.500 0.1637 0.00563 0.00204 0.0005 0.7855 0.8308
1.750 0.1908 0.00555 0.00200 0.0006 0.7781 0.8328
2.000 0.2182 0.00553 0.00199 0.0007 0.7711 0.8346
2.250 0.2450 0.00551 0.00198 0.0009 0.7605 0.8367
2.500 0.2714 0.00550 0.00200 0.0012 0.7483 0.8389
2.750 0.2963 0.00552 0.00199 0.0018 0.7253 0.8414
3.000 0.3157 0.00570 0.00196 0.0037 0.6682 0.8438
3.250 0.3329 0.00601 0.00203 0.0058 0.6017 0.8460
3.500 0.3477 0.00649 0.00221 0.0083 0.5143 0.8482
3.750 0.3598 0.00716 0.00245 0.0113 0.4024 0.8506
4.000 0.3728 0.00785 0.00272 0.0139 0.2955 0.8531
4.250 0.3864 0.00852 0.00298 0.0163 0.1976 0.8556
4.500 0.4024 0.00908 0.00323 0.0183 0.1243 0.8578
4.750 0.4186 0.00963 0.00351 0.0202 0.0615 0.8598
5.000 0.4377 0.01005 0.00378 0.0217 0.0301 0.8617
5.250 0.4584 0.01040 0.00413 0.0230 0.0205 0.8636
5.500 0.4806 0.01066 0.00442 0.0239 0.0180 0.8655
5.750 0.5023 0.01094 0.00474 0.0250 0.0162 0.8674
6.000 0.5229 0.01127 0.00507 0.0262 0.0140 0.8693
6.250 0.5352 0.01211 0.00605 0.0291 0.0126 0.8716
6.500 0.5570 0.01234 0.00629 0.0300 0.0123 0.8732
6.750 0.5781 0.01263 0.00664 0.0310 0.0118 0.8751
7.000 0.5984 0.01299 0.00705 0.0323 0.0107 0.8771
7.250 0.6143 0.01365 0.00779 0.0343 0.0110 0.8793
7.500 0.6318 0.01414 0.00834 0.0360 0.0104 0.8815
7.750 0.6490 0.01473 0.00900 0.0377 0.0103 0.8835
8.000 0.6662 0.01544 0.00975 0.0394 0.0095 0.8856
8.250 0.6846 0.01597 0.01029 0.0406 0.0088 0.8875
8.500 0.7051 0.01698 0.01142 0.0414 0.0087 0.8898
8.750 0.7315 0.01960 0.01425 0.0408 0.0084 0.8911
9.000 0.7533 0.02206 0.01694 0.0412 0.0083 0.8928
9.250 0.7705 0.02145 0.01637 0.0427 0.0079 0.8953
9.500 0.7866 0.02447 0.01970 0.0438 0.0081 0.8975
9.750 0.8033 0.02440 0.01973 0.0455 0.0076 0.9002
10.000 0.8154 0.02670 0.02231 0.0472 0.0075 0.9030
10.250 0.8278 0.02828 0.02412 0.0488 0.0071 0.9061
10.500 0.8238 0.03252 0.02880 0.0521 0.0071 0.9102
10.750 0.8421 0.03251 0.02882 0.0524 0.0066 0.9134
11.000 0.8131 0.04026 0.03722 0.0556 0.0072 0.9192
11.250 0.8055 0.04451 0.04178 0.0560 0.0068 0.9247
11.500 0.7909 0.04963 0.04720 0.0555 0.0068 0.9309
11.750 0.7550 0.05816 0.05608 0.0519 0.0075 0.9380
12.000 0.6282 0.04097 0.03881 0.0654 0.0078 0.9301
12.250 0.7288 0.07268 0.07102 0.0392 0.0073 0.9532
12.750 0.5869 0.05852 0.05676 0.0562 0.0072 0.9401
13.000 0.5657 0.06682 0.06516 0.0510 0.0074 0.9425
13.250 0.6457 0.12613 0.12462 0.0052 0.0090 1.0000
13.500 0.6348 0.13516 0.13363 0.0013 0.0093 1.0000
13.750 0.6449 0.13601 0.13449 0.0005 0.0088 1.0000
14.000 0.6433 0.14210 0.14057 -0.0023 0.0089 1.0000
14.250 0.3907 0.11792 0.11629 0.0319 0.0123 0.9348
|
Polar data table (+)
Polar graphs
<< Back to AH 85-L-120/17 (ah85l120-il)