AH 88-K-136/16 (ah88k136-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 88-K-136/16 (ah88k136-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.65 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah88k136-il-1000000.txt Download as CSV file: xf-ah88k136-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6021 0.04606 0.04345 -0.1046 0.7889 0.0083
-12.500 -0.6119 0.04335 0.04065 -0.1039 0.7881 0.0085
-12.250 -0.6803 0.03648 0.03337 -0.0977 0.7869 0.0082
-12.000 -0.6761 0.03554 0.03237 -0.0954 0.7863 0.0084
-11.750 -0.6932 0.03310 0.02970 -0.0904 0.7855 0.0085
-11.500 -0.7069 0.03094 0.02732 -0.0851 0.7847 0.0086
-11.250 -0.7173 0.02905 0.02522 -0.0797 0.7836 0.0086
-11.000 -0.7224 0.02752 0.02351 -0.0748 0.7823 0.0086
-10.750 -0.7191 0.02620 0.02201 -0.0712 0.7808 0.0088
-10.500 -0.7141 0.02463 0.02023 -0.0678 0.7795 0.0089
-10.250 -0.7027 0.02354 0.01896 -0.0654 0.7784 0.0091
-10.000 -0.6902 0.02241 0.01766 -0.0631 0.7774 0.0092
-9.750 -0.6738 0.02162 0.01672 -0.0614 0.7765 0.0093
-9.500 -0.6549 0.02106 0.01605 -0.0600 0.7757 0.0094
-9.250 -0.6472 0.01884 0.01356 -0.0569 0.7749 0.0102
-9.000 -0.6261 0.01841 0.01308 -0.0560 0.7742 0.0105
-8.750 -0.6051 0.01786 0.01245 -0.0550 0.7735 0.0108
-8.500 -0.5836 0.01729 0.01179 -0.0540 0.7729 0.0112
-8.250 -0.5613 0.01679 0.01120 -0.0531 0.7723 0.0117
-8.000 -0.5389 0.01629 0.01061 -0.0523 0.7718 0.0121
-7.750 -0.5150 0.01603 0.01028 -0.0516 0.7712 0.0125
-7.500 -0.4967 0.01501 0.00915 -0.0501 0.7704 0.0134
-7.250 -0.4735 0.01465 0.00877 -0.0494 0.7693 0.0140
-7.000 -0.4495 0.01438 0.00849 -0.0489 0.7679 0.0148
-6.750 -0.4256 0.01407 0.00814 -0.0482 0.7665 0.0155
-6.500 -0.4011 0.01384 0.00787 -0.0477 0.7654 0.0161
-6.250 -0.3799 0.01319 0.00717 -0.0466 0.7642 0.0175
-6.000 -0.3552 0.01295 0.00692 -0.0462 0.7633 0.0186
-5.750 -0.3303 0.01269 0.00663 -0.0457 0.7623 0.0198
-5.500 -0.3061 0.01233 0.00624 -0.0451 0.7615 0.0215
-5.250 -0.2816 0.01202 0.00592 -0.0446 0.7607 0.0235
-5.000 -0.2560 0.01182 0.00570 -0.0443 0.7601 0.0253
-4.750 -0.2318 0.01148 0.00533 -0.0437 0.7594 0.0282
-4.500 -0.2063 0.01125 0.00510 -0.0433 0.7588 0.0312
-4.250 -0.1811 0.01099 0.00482 -0.0429 0.7581 0.0348
-4.000 -0.1557 0.01079 0.00463 -0.0425 0.7574 0.0396
-3.750 -0.1307 0.01061 0.00445 -0.0420 0.7565 0.0454
-3.500 -0.1058 0.01050 0.00437 -0.0416 0.7552 0.0511
-3.250 -0.0814 0.01032 0.00425 -0.0411 0.7535 0.0605
-3.000 -0.0564 0.01017 0.00414 -0.0406 0.7519 0.0711
-2.750 -0.0312 0.00999 0.00401 -0.0403 0.7504 0.0849
-2.500 -0.0058 0.00977 0.00386 -0.0399 0.7491 0.1052
-2.250 0.0194 0.00951 0.00370 -0.0395 0.7479 0.1349
-2.000 0.0440 0.00918 0.00352 -0.0390 0.7468 0.1793
-1.750 0.0667 0.00874 0.00332 -0.0382 0.7457 0.2566
-1.500 0.0817 0.00794 0.00309 -0.0359 0.7446 0.4332
-1.250 0.0873 0.00707 0.00287 -0.0314 0.7433 0.6294
-1.000 0.0872 0.00629 0.00289 -0.0251 0.7412 0.8326
-0.750 0.1183 0.00642 0.00315 -0.0256 0.7390 0.8922
-0.500 0.1437 0.00650 0.00323 -0.0249 0.7367 0.9065
-0.250 0.1709 0.00658 0.00328 -0.0246 0.7348 0.9160
0.000 0.1994 0.00674 0.00342 -0.0245 0.7331 0.9261
0.250 0.2448 0.00700 0.00365 -0.0281 0.7318 0.9318
0.500 0.3047 0.00734 0.00394 -0.0349 0.7306 0.9349
0.750 0.3635 0.00757 0.00413 -0.0417 0.7292 0.9363
1.000 0.3928 0.00783 0.00438 -0.0418 0.7269 0.9440
1.250 0.4427 0.00795 0.00451 -0.0468 0.7243 0.9448
1.500 0.4784 0.00791 0.00447 -0.0487 0.7215 0.9455
1.750 0.5136 0.00786 0.00440 -0.0504 0.7189 0.9462
2.000 0.5479 0.00779 0.00432 -0.0520 0.7161 0.9470
2.250 0.5812 0.00777 0.00428 -0.0534 0.7130 0.9479
2.500 0.6129 0.00776 0.00431 -0.0545 0.7092 0.9491
2.750 0.6434 0.00773 0.00428 -0.0553 0.7048 0.9505
3.000 0.6716 0.00767 0.00421 -0.0555 0.7006 0.9521
3.250 0.6926 0.00766 0.00423 -0.0542 0.6955 0.9550
3.500 0.7050 0.00761 0.00419 -0.0510 0.6889 0.9586
3.750 0.7358 0.00755 0.00414 -0.0519 0.6830 0.9591
4.000 0.7670 0.00753 0.00414 -0.0529 0.6753 0.9597
4.250 0.7978 0.00751 0.00413 -0.0538 0.6667 0.9603
4.500 0.8270 0.00752 0.00411 -0.0544 0.6550 0.9610
4.750 0.8546 0.00755 0.00414 -0.0546 0.6405 0.9617
5.000 0.8785 0.00773 0.00421 -0.0541 0.6064 0.9630
5.250 0.8959 0.00813 0.00441 -0.0523 0.5587 0.9650
5.500 0.9023 0.00868 0.00473 -0.0483 0.5070 0.9681
5.750 0.9016 0.00911 0.00503 -0.0427 0.4727 0.9720
6.250 0.9392 0.01032 0.00583 -0.0409 0.3800 0.9744
6.500 0.9549 0.01104 0.00634 -0.0395 0.3333 0.9761
6.750 0.9669 0.01175 0.00687 -0.0374 0.2929 0.9785
7.000 0.9651 0.01242 0.00741 -0.0324 0.2621 0.9822
7.250 0.9665 0.01317 0.00800 -0.0286 0.2256 0.9850
7.500 0.9718 0.01440 0.00896 -0.0267 0.1744 0.9874
7.750 0.9768 0.01552 0.00984 -0.0244 0.1300 0.9897
8.000 0.9754 0.01689 0.01090 -0.0211 0.0763 0.9923
8.250 0.9798 0.01807 0.01186 -0.0185 0.0391 0.9942
8.500 0.9952 0.01898 0.01268 -0.0178 0.0244 0.9952
8.750 1.0133 0.01964 0.01335 -0.0174 0.0206 0.9962
9.000 1.0300 0.02039 0.01409 -0.0167 0.0176 0.9972
9.250 1.0481 0.02105 0.01479 -0.0162 0.0158 0.9981
9.500 1.0662 0.02174 0.01552 -0.0158 0.0146 0.9989
9.750 1.0817 0.02266 0.01646 -0.0152 0.0132 0.9997
10.000 1.0928 0.02350 0.01735 -0.0136 0.0126 1.0000
10.250 1.0992 0.02414 0.01803 -0.0108 0.0120 1.0000
10.500 1.1048 0.02481 0.01874 -0.0080 0.0115 1.0000
10.750 1.1098 0.02551 0.01948 -0.0051 0.0111 1.0000
11.000 1.1148 0.02619 0.02019 -0.0023 0.0106 1.0000
11.250 1.1115 0.02729 0.02133 0.0016 0.0098 1.0000
11.500 1.1088 0.02840 0.02251 0.0053 0.0097 1.0000
11.750 1.1140 0.02916 0.02331 0.0079 0.0094 1.0000
12.000 1.1199 0.03016 0.02436 0.0101 0.0092 1.0000
12.250 1.1272 0.03128 0.02554 0.0118 0.0089 1.0000
12.500 1.1351 0.03250 0.02682 0.0133 0.0086 1.0000
12.750 1.1456 0.03361 0.02796 0.0144 0.0082 1.0000
13.000 1.1551 0.03481 0.02921 0.0154 0.0078 1.0000
13.250 1.1630 0.03621 0.03065 0.0166 0.0076 1.0000
13.500 1.1661 0.03806 0.03258 0.0180 0.0075 1.0000
13.750 1.1622 0.04056 0.03517 0.0196 0.0071 1.0000
14.000 1.1653 0.04253 0.03722 0.0208 0.0069 1.0000
14.250 1.1700 0.04442 0.03920 0.0217 0.0068 1.0000
14.500 1.1744 0.04637 0.04121 0.0225 0.0068 1.0000
14.750 1.1852 0.04782 0.04274 0.0228 0.0065 1.0000
15.000 1.1871 0.05010 0.04512 0.0236 0.0064 1.0000
15.250 1.1939 0.05199 0.04708 0.0239 0.0062 1.0000
15.500 1.1920 0.05474 0.04994 0.0248 0.0063 1.0000
15.750 1.1974 0.05690 0.05217 0.0249 0.0060 1.0000
16.000 1.1976 0.05958 0.05495 0.0253 0.0060 1.0000
16.250 1.2012 0.06203 0.05748 0.0252 0.0058 1.0000
16.500 1.2012 0.06489 0.06043 0.0252 0.0057 1.0000
16.750 1.2072 0.06728 0.06285 0.0245 0.0054 1.0000
17.000 1.2000 0.07100 0.06674 0.0249 0.0056 1.0000
17.250 1.1986 0.07425 0.07009 0.0245 0.0055 1.0000
17.500 1.2002 0.07733 0.07319 0.0234 0.0052 1.0000
17.750 1.1952 0.08116 0.07716 0.0229 0.0053 1.0000
18.000 1.1787 0.08651 0.08265 0.0222 0.0050 1.0000
18.250 1.1576 0.09262 0.08897 0.0214 0.0049 1.0000
18.500 1.1748 0.09399 0.09033 0.0198 0.0052 1.0000
18.750 1.1486 0.10121 0.09776 0.0182 0.0049 1.0000
19.000 1.1372 0.10680 0.10350 0.0160 0.0049 1.0000
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