AH 93-K-131/15 (ah93k131-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-K-131/15 (ah93k131-il) Reynolds number: 1,000,000 Max Cl/Cd: 138.31 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93k131-il-1000000.txt Download as CSV file: xf-ah93k131-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-131/15
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3206 0.11630 0.11422 -0.0147 0.7743 0.0127
-11.000 -0.3211 0.11236 0.11028 -0.0160 0.7736 0.0133
-8.750 -0.6948 0.02667 0.02279 -0.0306 0.7682 0.0100
-8.500 -0.6822 0.02385 0.01958 -0.0288 0.7669 0.0102
-8.250 -0.6626 0.02232 0.01781 -0.0278 0.7655 0.0105
-8.000 -0.6397 0.02139 0.01670 -0.0272 0.7641 0.0107
-7.750 -0.6263 0.01836 0.01323 -0.0252 0.7626 0.0114
-7.500 -0.6006 0.01801 0.01285 -0.0250 0.7613 0.0118
-7.250 -0.5747 0.01768 0.01247 -0.0249 0.7601 0.0122
-7.000 -0.5494 0.01714 0.01183 -0.0246 0.7589 0.0126
-6.750 -0.5244 0.01641 0.01098 -0.0242 0.7577 0.0131
-6.500 -0.4990 0.01577 0.01020 -0.0238 0.7563 0.0136
-6.250 -0.4727 0.01524 0.00957 -0.0236 0.7549 0.0140
-6.000 -0.4455 0.01490 0.00916 -0.0236 0.7536 0.0143
-5.750 -0.4227 0.01345 0.00758 -0.0228 0.7521 0.0154
-5.500 -0.3956 0.01315 0.00726 -0.0228 0.7505 0.0162
-5.250 -0.3682 0.01291 0.00700 -0.0228 0.7489 0.0171
-5.000 -0.3408 0.01265 0.00670 -0.0228 0.7474 0.0180
-4.750 -0.3133 0.01241 0.00641 -0.0228 0.7460 0.0187
-4.500 -0.2888 0.01159 0.00549 -0.0222 0.7446 0.0201
-4.250 -0.2619 0.01128 0.00517 -0.0221 0.7432 0.0213
-4.000 -0.2346 0.01109 0.00495 -0.0221 0.7415 0.0225
-3.750 -0.2067 0.01087 0.00471 -0.0222 0.7400 0.0239
-3.500 -0.1782 0.01076 0.00461 -0.0224 0.7383 0.0248
-3.250 -0.1527 0.01018 0.00398 -0.0220 0.7364 0.0273
-3.000 -0.1250 0.00996 0.00376 -0.0221 0.7346 0.0292
-2.750 -0.0972 0.00978 0.00356 -0.0221 0.7328 0.0312
-2.500 -0.0690 0.00965 0.00342 -0.0223 0.7311 0.0325
-2.250 -0.0424 0.00929 0.00301 -0.0220 0.7294 0.0368
-2.000 -0.0147 0.00915 0.00285 -0.0221 0.7275 0.0403
-1.750 0.0135 0.00900 0.00271 -0.0223 0.7257 0.0444
-1.500 0.0413 0.00880 0.00255 -0.0224 0.7237 0.0534
-1.250 0.0689 0.00857 0.00241 -0.0224 0.7215 0.0745
-1.000 0.0951 0.00821 0.00227 -0.0223 0.7192 0.1419
-0.750 0.1192 0.00765 0.00214 -0.0219 0.7171 0.2750
-0.500 0.1401 0.00690 0.00200 -0.0208 0.7150 0.4744
-0.250 0.1508 0.00585 0.00188 -0.0174 0.7125 0.7489
0.000 0.2111 0.00573 0.00238 -0.0241 0.7107 0.9395
0.250 0.2365 0.00588 0.00250 -0.0234 0.7080 0.9542
0.500 0.2753 0.00610 0.00268 -0.0256 0.7055 0.9635
0.750 0.3226 0.00641 0.00296 -0.0296 0.7032 0.9739
1.000 0.3811 0.00674 0.00323 -0.0361 0.7011 0.9846
1.250 0.4388 0.00674 0.00318 -0.0427 0.6985 0.9893
1.500 0.4766 0.00671 0.00316 -0.0451 0.6950 0.9927
1.750 0.5100 0.00666 0.00311 -0.0465 0.6911 0.9945
2.000 0.5450 0.00657 0.00298 -0.0483 0.6875 0.9954
2.250 0.5791 0.00651 0.00290 -0.0499 0.6835 0.9964
2.500 0.6130 0.00645 0.00285 -0.0515 0.6789 0.9975
2.750 0.6464 0.00639 0.00279 -0.0529 0.6744 0.9986
3.000 0.6796 0.00635 0.00273 -0.0544 0.6698 0.9996
3.250 0.7102 0.00632 0.00272 -0.0553 0.6641 1.0000
3.500 0.7378 0.00632 0.00270 -0.0555 0.6584 1.0000
3.750 0.7657 0.00632 0.00272 -0.0558 0.6516 1.0000
4.000 0.7935 0.00634 0.00272 -0.0561 0.6437 1.0000
4.250 0.8214 0.00636 0.00275 -0.0564 0.6349 1.0000
4.500 0.8493 0.00641 0.00279 -0.0567 0.6254 1.0000
4.750 0.8774 0.00649 0.00284 -0.0571 0.6103 1.0000
5.000 0.9055 0.00661 0.00292 -0.0576 0.5933 1.0000
5.250 0.9336 0.00675 0.00303 -0.0580 0.5773 1.0000
5.500 0.9618 0.00697 0.00318 -0.0586 0.5563 1.0000
5.750 0.9898 0.00725 0.00338 -0.0592 0.5297 1.0000
6.000 1.0174 0.00760 0.00363 -0.0598 0.5009 1.0000
6.250 1.0445 0.00802 0.00394 -0.0604 0.4698 1.0000
6.500 1.0708 0.00854 0.00430 -0.0609 0.4332 1.0000
6.750 1.0955 0.00918 0.00476 -0.0613 0.3919 1.0000
7.000 1.1168 0.01014 0.00542 -0.0614 0.3328 1.0000
7.250 1.1351 0.01110 0.00612 -0.0609 0.2803 1.0000
7.500 1.1499 0.01215 0.00691 -0.0599 0.2303 1.0000
7.750 1.1607 0.01328 0.00779 -0.0583 0.1858 1.0000
8.000 1.1673 0.01438 0.00871 -0.0559 0.1523 1.0000
8.250 1.1669 0.01533 0.00956 -0.0520 0.1304 1.0000
8.500 1.1575 0.01610 0.01026 -0.0459 0.1160 1.0000
8.750 1.1556 0.01689 0.01100 -0.0415 0.1005 1.0000
9.000 1.1573 0.01769 0.01173 -0.0377 0.0864 1.0000
9.250 1.1609 0.01849 0.01247 -0.0344 0.0735 1.0000
9.500 1.1659 0.01928 0.01320 -0.0313 0.0622 1.0000
9.750 1.1713 0.02008 0.01397 -0.0285 0.0522 1.0000
10.000 1.1777 0.02089 0.01473 -0.0258 0.0437 1.0000
10.250 1.1835 0.02176 0.01556 -0.0231 0.0361 1.0000
10.500 1.1913 0.02256 0.01635 -0.0207 0.0305 1.0000
10.750 1.1986 0.02343 0.01722 -0.0184 0.0252 1.0000
11.000 1.2053 0.02439 0.01816 -0.0161 0.0202 1.0000
11.250 1.2119 0.02540 0.01915 -0.0139 0.0164 1.0000
11.500 1.2200 0.02636 0.02015 -0.0119 0.0141 1.0000
11.750 1.2258 0.02752 0.02131 -0.0098 0.0119 1.0000
12.000 1.2341 0.02858 0.02242 -0.0080 0.0109 1.0000
12.250 1.2437 0.02961 0.02350 -0.0066 0.0100 1.0000
12.500 1.2514 0.03086 0.02479 -0.0050 0.0091 1.0000
12.750 1.2552 0.03248 0.02648 -0.0032 0.0083 1.0000
13.000 1.2659 0.03363 0.02768 -0.0022 0.0080 1.0000
13.250 1.2752 0.03491 0.02902 -0.0011 0.0076 1.0000
13.500 1.2836 0.03632 0.03049 0.0000 0.0073 1.0000
13.750 1.2917 0.03780 0.03202 0.0010 0.0070 1.0000
14.000 1.2988 0.03941 0.03369 0.0019 0.0067 1.0000
14.250 1.3038 0.04123 0.03558 0.0029 0.0064 1.0000
14.500 1.3047 0.04351 0.03794 0.0041 0.0061 1.0000
14.750 1.2997 0.04643 0.04099 0.0054 0.0059 1.0000
15.000 1.3029 0.04862 0.04326 0.0061 0.0058 1.0000
15.250 1.3077 0.05069 0.04542 0.0066 0.0057 1.0000
15.500 1.3112 0.05296 0.04777 0.0071 0.0056 1.0000
15.750 1.3141 0.05536 0.05026 0.0075 0.0055 1.0000
16.000 1.3158 0.05792 0.05291 0.0079 0.0054 1.0000
16.250 1.3166 0.06064 0.05572 0.0081 0.0053 1.0000
16.500 1.3166 0.06352 0.05869 0.0083 0.0052 1.0000
16.750 1.3159 0.06655 0.06182 0.0083 0.0051 1.0000
17.000 1.3146 0.06972 0.06508 0.0081 0.0050 1.0000
17.250 1.3125 0.07304 0.06850 0.0079 0.0049 1.0000
17.500 1.3096 0.07653 0.07209 0.0076 0.0049 1.0000
17.750 1.3060 0.08020 0.07587 0.0070 0.0048 1.0000
18.000 1.3019 0.08403 0.07980 0.0063 0.0047 1.0000
18.250 1.2969 0.08804 0.08391 0.0055 0.0047 1.0000
18.500 1.2910 0.09224 0.08821 0.0045 0.0046 1.0000
18.750 1.2843 0.09665 0.09272 0.0034 0.0046 1.0000
19.000 1.2775 0.10117 0.09734 0.0020 0.0045 1.0000
19.250 1.2698 0.10592 0.10219 0.0005 0.0044 1.0000
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Polar data table (+)
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