AH 88-K-136/16 (ah88k136-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 88-K-136/16 (ah88k136-il) Reynolds number: 500,000 Max Cl/Cd: 87.07 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah88k136-il-500000-n5.txt Download as CSV file: xf-ah88k136-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 88-K-136/16
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6525 0.04444 0.04093 -0.0995 0.7843 0.0075
-12.500 -0.6586 0.04229 0.03871 -0.0980 0.7833 0.0077
-12.250 -0.6991 0.03742 0.03351 -0.0932 0.7814 0.0076
-12.000 -0.6968 0.03621 0.03222 -0.0908 0.7800 0.0077
-11.750 -0.6987 0.03469 0.03058 -0.0877 0.7786 0.0080
-11.500 -0.7047 0.03282 0.02850 -0.0837 0.7773 0.0081
-11.250 -0.7102 0.03097 0.02643 -0.0794 0.7762 0.0082
-11.000 -0.7119 0.02946 0.02471 -0.0752 0.7752 0.0083
-10.750 -0.7083 0.02816 0.02320 -0.0718 0.7743 0.0085
-10.500 -0.7022 0.02663 0.02140 -0.0688 0.7735 0.0088
-10.250 -0.6919 0.02532 0.01986 -0.0663 0.7729 0.0090
-10.000 -0.6798 0.02407 0.01839 -0.0640 0.7722 0.0092
-9.750 -0.6642 0.02309 0.01721 -0.0622 0.7716 0.0094
-9.500 -0.6493 0.02197 0.01591 -0.0603 0.7710 0.0096
-9.250 -0.6313 0.02129 0.01515 -0.0590 0.7705 0.0101
-9.000 -0.6126 0.02060 0.01437 -0.0577 0.7690 0.0103
-8.750 -0.5928 0.01998 0.01365 -0.0565 0.7675 0.0106
-8.500 -0.5721 0.01940 0.01298 -0.0555 0.7662 0.0111
-8.250 -0.5508 0.01883 0.01231 -0.0545 0.7650 0.0116
-8.000 -0.5292 0.01826 0.01162 -0.0536 0.7639 0.0120
-7.750 -0.5068 0.01774 0.01100 -0.0528 0.7628 0.0125
-7.500 -0.4851 0.01714 0.01035 -0.0519 0.7618 0.0133
-7.250 -0.4618 0.01675 0.00991 -0.0513 0.7609 0.0140
-7.000 -0.4381 0.01641 0.00951 -0.0507 0.7602 0.0150
-6.750 -0.4146 0.01599 0.00901 -0.0500 0.7595 0.0158
-6.500 -0.3917 0.01550 0.00847 -0.0493 0.7589 0.0168
-6.250 -0.3679 0.01511 0.00804 -0.0487 0.7583 0.0178
-6.000 -0.3436 0.01480 0.00768 -0.0482 0.7577 0.0192
-5.750 -0.3191 0.01449 0.00730 -0.0476 0.7571 0.0205
-5.500 -0.2955 0.01408 0.00687 -0.0470 0.7565 0.0222
-5.250 -0.2722 0.01391 0.00671 -0.0463 0.7545 0.0240
-5.000 -0.2483 0.01375 0.00652 -0.0457 0.7526 0.0258
-4.750 -0.2245 0.01348 0.00627 -0.0451 0.7510 0.0287
-4.500 -0.2000 0.01328 0.00605 -0.0446 0.7497 0.0318
-4.250 -0.1756 0.01304 0.00581 -0.0441 0.7485 0.0355
-4.000 -0.1508 0.01284 0.00560 -0.0436 0.7476 0.0398
-3.750 -0.1261 0.01261 0.00539 -0.0432 0.7466 0.0454
-3.500 -0.1008 0.01241 0.00517 -0.0428 0.7457 0.0511
-3.250 -0.0758 0.01218 0.00496 -0.0423 0.7449 0.0591
-3.000 -0.0505 0.01197 0.00477 -0.0419 0.7442 0.0685
-2.750 -0.0252 0.01175 0.00457 -0.0416 0.7435 0.0810
-2.500 0.0001 0.01154 0.00439 -0.0412 0.7428 0.0963
-2.250 0.0239 0.01142 0.00436 -0.0406 0.7409 0.1170
-2.000 0.0469 0.01131 0.00438 -0.0399 0.7382 0.1456
-1.750 0.0703 0.01109 0.00430 -0.0393 0.7361 0.1866
-1.500 0.0921 0.01070 0.00416 -0.0383 0.7344 0.2595
-1.250 0.1076 0.00997 0.00397 -0.0361 0.7328 0.4178
-1.000 0.1159 0.00915 0.00375 -0.0322 0.7313 0.5892
-0.750 0.1673 0.00852 0.00416 -0.0368 0.7305 0.8676
-0.500 0.1839 0.00863 0.00423 -0.0340 0.7293 0.8947
-0.250 0.2086 0.00877 0.00433 -0.0331 0.7279 0.9088
0.000 0.2453 0.00917 0.00474 -0.0349 0.7241 0.9179
0.250 0.2614 0.00929 0.00485 -0.0322 0.7209 0.9282
0.500 0.3357 0.00965 0.00517 -0.0420 0.7193 0.9312
0.750 0.3782 0.00970 0.00518 -0.0452 0.7174 0.9334
1.000 0.4095 0.00961 0.00506 -0.0461 0.7154 0.9351
1.250 0.4384 0.00954 0.00497 -0.0464 0.7132 0.9372
1.500 0.4460 0.00962 0.00508 -0.0422 0.7084 0.9435
1.750 0.4787 0.00957 0.00503 -0.0435 0.7048 0.9441
2.000 0.5109 0.00947 0.00491 -0.0446 0.7018 0.9448
2.250 0.5424 0.00938 0.00480 -0.0456 0.6988 0.9455
2.500 0.5714 0.00942 0.00489 -0.0462 0.6929 0.9464
2.750 0.6012 0.00936 0.00483 -0.0468 0.6884 0.9473
3.000 0.6304 0.00929 0.00475 -0.0472 0.6836 0.9483
3.250 0.6573 0.00930 0.00480 -0.0473 0.6765 0.9495
3.500 0.6845 0.00921 0.00469 -0.0474 0.6703 0.9507
3.750 0.7093 0.00923 0.00474 -0.0470 0.6606 0.9525
4.000 0.7307 0.00921 0.00472 -0.0458 0.6513 0.9544
4.250 0.7405 0.00919 0.00468 -0.0420 0.6396 0.9581
4.500 0.7684 0.00921 0.00467 -0.0423 0.6236 0.9587
4.750 0.7949 0.00929 0.00470 -0.0423 0.6050 0.9593
5.000 0.8195 0.00943 0.00479 -0.0420 0.5829 0.9602
5.250 0.8420 0.00967 0.00494 -0.0413 0.5576 0.9613
5.500 0.8624 0.01002 0.00519 -0.0403 0.5283 0.9628
5.750 0.8768 0.01053 0.00555 -0.0381 0.4920 0.9651
6.000 0.8787 0.01121 0.00603 -0.0337 0.4477 0.9688
6.250 0.8802 0.01197 0.00659 -0.0294 0.4068 0.9723
6.500 0.8904 0.01306 0.00742 -0.0276 0.3523 0.9746
6.750 0.8923 0.01396 0.00814 -0.0242 0.3144 0.9779
7.000 0.8881 0.01497 0.00897 -0.0198 0.2754 0.9822
7.250 0.8964 0.01596 0.00977 -0.0179 0.2371 0.9846
7.500 0.9067 0.01705 0.01062 -0.0166 0.1903 0.9862
7.750 0.9155 0.01818 0.01149 -0.0151 0.1422 0.9880
8.000 0.9240 0.01931 0.01239 -0.0134 0.0999 0.9899
8.250 0.9319 0.02046 0.01333 -0.0116 0.0615 0.9918
8.500 0.9414 0.02153 0.01425 -0.0100 0.0363 0.9934
8.750 0.9568 0.02234 0.01504 -0.0091 0.0277 0.9950
9.000 0.9733 0.02317 0.01585 -0.0086 0.0218 0.9967
9.250 0.9910 0.02389 0.01660 -0.0081 0.0188 0.9979
9.500 1.0074 0.02475 0.01747 -0.0076 0.0166 0.9990
9.750 1.0252 0.02554 0.01833 -0.0073 0.0153 0.9998
10.000 1.0342 0.02627 0.01911 -0.0052 0.0145 1.0000
10.250 1.0390 0.02703 0.01990 -0.0023 0.0135 1.0000
10.500 1.0417 0.02791 0.02081 0.0008 0.0127 1.0000
10.750 1.0473 0.02866 0.02162 0.0034 0.0121 1.0000
11.000 1.0537 0.02942 0.02243 0.0058 0.0115 1.0000
11.250 1.0600 0.03028 0.02334 0.0081 0.0108 1.0000
11.500 1.0666 0.03127 0.02438 0.0102 0.0104 1.0000
11.750 1.0731 0.03240 0.02556 0.0121 0.0100 1.0000
12.000 1.0769 0.03386 0.02707 0.0140 0.0096 1.0000
12.250 1.0851 0.03506 0.02834 0.0154 0.0093 1.0000
12.500 1.0921 0.03642 0.02978 0.0168 0.0089 1.0000
12.750 1.0998 0.03778 0.03121 0.0180 0.0086 1.0000
13.000 1.1075 0.03919 0.03268 0.0191 0.0082 1.0000
13.250 1.1154 0.04063 0.03419 0.0201 0.0079 1.0000
13.500 1.1192 0.04248 0.03613 0.0213 0.0078 1.0000
13.750 1.1279 0.04392 0.03761 0.0220 0.0073 1.0000
14.000 1.1294 0.04610 0.03984 0.0230 0.0070 1.0000
14.250 1.1322 0.04822 0.04207 0.0239 0.0068 1.0000
14.500 1.1368 0.05021 0.04414 0.0245 0.0069 1.0000
14.750 1.1432 0.05208 0.04611 0.0250 0.0065 1.0000
15.000 1.1456 0.05440 0.04854 0.0256 0.0063 1.0000
15.250 1.1488 0.05671 0.05095 0.0259 0.0062 1.0000
15.500 1.1485 0.05944 0.05379 0.0263 0.0063 1.0000
15.750 1.1513 0.06191 0.05636 0.0264 0.0059 1.0000
16.000 1.1518 0.06469 0.05925 0.0265 0.0058 1.0000
16.250 1.1533 0.06745 0.06210 0.0264 0.0057 1.0000
16.500 1.1534 0.07043 0.06518 0.0261 0.0055 1.0000
16.750 1.1553 0.07329 0.06813 0.0257 0.0054 1.0000
17.000 1.1510 0.07690 0.07185 0.0253 0.0054 1.0000
17.250 1.1493 0.08032 0.07539 0.0247 0.0053 1.0000
17.500 1.1486 0.08372 0.07887 0.0238 0.0052 1.0000
17.750 1.1437 0.08771 0.08298 0.0229 0.0052 1.0000
18.000 1.1375 0.09198 0.08734 0.0216 0.0050 1.0000
18.250 1.1283 0.09673 0.09220 0.0203 0.0049 1.0000
18.500 1.1252 0.10074 0.09636 0.0190 0.0050 1.0000
18.750 1.1143 0.10596 0.10171 0.0173 0.0049 1.0000
19.000 1.1086 0.11056 0.10643 0.0155 0.0049 1.0000
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