PT40 (pt40-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: PT40 (pt40-il) Reynolds number: 500,000 Max Cl/Cd: 76.13 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pt40-il-500000-n5.txt Download as CSV file: xf-pt40-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: PT40
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4229 0.12775 0.12481 -0.0184 1.0000 0.0302
-11.500 -0.4188 0.12426 0.12132 -0.0197 1.0000 0.0305
-9.500 -0.7212 0.03101 0.02676 -0.0715 0.9936 0.0394
-9.250 -0.6945 0.02990 0.02557 -0.0724 0.9908 0.0396
-9.000 -0.6662 0.02893 0.02454 -0.0735 0.9878 0.0397
-8.750 -0.6365 0.02796 0.02349 -0.0747 0.9852 0.0399
-8.500 -0.6061 0.02686 0.02230 -0.0761 0.9830 0.0401
-8.250 -0.5794 0.02565 0.02097 -0.0768 0.9790 0.0404
-8.000 -0.5520 0.02413 0.01929 -0.0777 0.9749 0.0408
-7.750 -0.5227 0.02245 0.01738 -0.0790 0.9719 0.0414
-7.500 -0.4970 0.02057 0.01522 -0.0795 0.9666 0.0422
-7.250 -0.4708 0.01875 0.01305 -0.0799 0.9605 0.0429
-7.000 -0.4407 0.01762 0.01171 -0.0807 0.9554 0.0434
-6.750 -0.4120 0.01707 0.01114 -0.0808 0.9474 0.0436
-6.500 -0.3800 0.01661 0.01065 -0.0816 0.9410 0.0439
-6.250 -0.3504 0.01619 0.01021 -0.0818 0.9314 0.0442
-6.000 -0.3198 0.01577 0.00973 -0.0822 0.9219 0.0445
-5.750 -0.2898 0.01533 0.00923 -0.0825 0.9110 0.0449
-5.500 -0.2612 0.01488 0.00870 -0.0824 0.8981 0.0454
-5.250 -0.2329 0.01445 0.00817 -0.0823 0.8852 0.0459
-5.000 -0.2051 0.01402 0.00761 -0.0820 0.8719 0.0466
-4.750 -0.1778 0.01359 0.00705 -0.0816 0.8582 0.0471
-4.500 -0.1506 0.01321 0.00654 -0.0812 0.8452 0.0476
-4.250 -0.1234 0.01289 0.00618 -0.0808 0.8326 0.0480
-4.000 -0.0960 0.01266 0.00592 -0.0804 0.8203 0.0484
-3.750 -0.0685 0.01246 0.00568 -0.0801 0.8087 0.0488
-3.500 -0.0411 0.01225 0.00543 -0.0797 0.7968 0.0493
-3.250 -0.0135 0.01204 0.00517 -0.0793 0.7864 0.0499
-3.000 0.0140 0.01183 0.00490 -0.0789 0.7752 0.0505
-2.750 0.0416 0.01162 0.00463 -0.0785 0.7648 0.0512
-2.500 0.0692 0.01144 0.00438 -0.0781 0.7542 0.0519
-2.250 0.0968 0.01123 0.00416 -0.0778 0.7439 0.0526
-2.000 0.1239 0.01112 0.00400 -0.0773 0.7290 0.0532
-1.750 0.1508 0.01102 0.00384 -0.0767 0.7095 0.0539
-1.500 0.1776 0.01093 0.00368 -0.0762 0.6887 0.0546
-1.250 0.2045 0.01085 0.00352 -0.0756 0.6678 0.0554
-1.000 0.2313 0.01077 0.00336 -0.0751 0.6465 0.0563
-0.750 0.2585 0.01071 0.00322 -0.0746 0.6276 0.0571
-0.500 0.2856 0.01061 0.00311 -0.0742 0.6099 0.0580
-0.250 0.3129 0.01058 0.00304 -0.0737 0.5919 0.0591
0.000 0.3400 0.01056 0.00297 -0.0733 0.5730 0.0602
0.250 0.3670 0.01055 0.00290 -0.0728 0.5541 0.0613
0.500 0.3940 0.01057 0.00284 -0.0723 0.5338 0.0624
0.750 0.4208 0.01056 0.00279 -0.0718 0.5138 0.0636
1.000 0.4477 0.01061 0.00279 -0.0713 0.4928 0.0650
1.250 0.4743 0.01069 0.00280 -0.0708 0.4690 0.0667
1.500 0.5008 0.01080 0.00281 -0.0703 0.4437 0.0683
1.750 0.5270 0.01090 0.00283 -0.0697 0.4142 0.0699
2.000 0.5526 0.01110 0.00290 -0.0691 0.3770 0.0718
2.250 0.5776 0.01138 0.00299 -0.0684 0.3351 0.0740
2.500 0.6029 0.01163 0.00311 -0.0677 0.3002 0.0766
2.750 0.6285 0.01186 0.00324 -0.0671 0.2738 0.0797
3.000 0.6545 0.01206 0.00336 -0.0665 0.2528 0.0831
3.250 0.6804 0.01226 0.00350 -0.0660 0.2336 0.0882
3.500 0.7062 0.01246 0.00364 -0.0654 0.2160 0.0958
4.000 0.7485 0.01102 0.00412 -0.0631 0.1918 0.8250
4.250 0.7852 0.01101 0.00430 -0.0644 0.1814 1.0000
4.500 0.8106 0.01126 0.00446 -0.0637 0.1730 1.0000
4.750 0.8364 0.01148 0.00462 -0.0631 0.1652 1.0000
5.000 0.8618 0.01173 0.00480 -0.0625 0.1578 1.0000
5.250 0.8874 0.01197 0.00499 -0.0618 0.1503 1.0000
5.500 0.9128 0.01223 0.00518 -0.0612 0.1437 1.0000
5.750 0.9380 0.01250 0.00539 -0.0605 0.1360 1.0000
6.000 0.9634 0.01275 0.00560 -0.0598 0.1299 1.0000
6.250 0.9882 0.01305 0.00584 -0.0591 0.1230 1.0000
6.500 1.0132 0.01332 0.00607 -0.0584 0.1157 1.0000
6.750 1.0377 0.01363 0.00633 -0.0577 0.1074 1.0000
7.000 1.0616 0.01398 0.00662 -0.0569 0.0977 1.0000
7.250 1.0848 0.01440 0.00694 -0.0560 0.0857 1.0000
7.500 1.1068 0.01492 0.00734 -0.0549 0.0701 1.0000
7.750 1.1279 0.01549 0.00780 -0.0537 0.0575 1.0000
8.000 1.1497 0.01600 0.00825 -0.0526 0.0511 1.0000
8.250 1.1716 0.01646 0.00869 -0.0515 0.0475 1.0000
8.500 1.1934 0.01693 0.00915 -0.0504 0.0450 1.0000
8.750 1.2151 0.01739 0.00960 -0.0493 0.0433 1.0000
9.000 1.2365 0.01784 0.01005 -0.0482 0.0418 1.0000
9.250 1.2571 0.01834 0.01056 -0.0470 0.0405 1.0000
9.500 1.2771 0.01886 0.01108 -0.0456 0.0395 1.0000
9.750 1.2972 0.01933 0.01157 -0.0444 0.0386 1.0000
10.000 1.3162 0.01984 0.01210 -0.0429 0.0378 1.0000
10.250 1.3331 0.02037 0.01266 -0.0411 0.0371 1.0000
10.500 1.3492 0.02097 0.01327 -0.0392 0.0365 1.0000
10.750 1.3642 0.02163 0.01396 -0.0373 0.0359 1.0000
11.000 1.3788 0.02233 0.01468 -0.0354 0.0355 1.0000
11.250 1.3942 0.02298 0.01537 -0.0336 0.0351 1.0000
11.500 1.4088 0.02369 0.01613 -0.0319 0.0347 1.0000
11.750 1.4226 0.02447 0.01696 -0.0301 0.0342 1.0000
12.000 1.4358 0.02531 0.01785 -0.0284 0.0339 1.0000
12.250 1.4481 0.02622 0.01881 -0.0267 0.0335 1.0000
12.500 1.4597 0.02722 0.01986 -0.0251 0.0332 1.0000
12.750 1.4704 0.02833 0.02102 -0.0235 0.0329 1.0000
13.000 1.4800 0.02955 0.02230 -0.0219 0.0326 1.0000
13.250 1.4885 0.03092 0.02372 -0.0205 0.0323 1.0000
13.500 1.4954 0.03247 0.02532 -0.0192 0.0321 1.0000
13.750 1.5006 0.03423 0.02715 -0.0179 0.0318 1.0000
14.000 1.5064 0.03603 0.02901 -0.0169 0.0316 1.0000
14.250 1.5132 0.03778 0.03085 -0.0160 0.0314 1.0000
14.500 1.5191 0.03971 0.03285 -0.0153 0.0312 1.0000
14.750 1.5238 0.04179 0.03503 -0.0147 0.0310 1.0000
15.000 1.5274 0.04406 0.03738 -0.0143 0.0307 1.0000
15.250 1.5297 0.04653 0.03994 -0.0140 0.0305 1.0000
15.500 1.5308 0.04922 0.04272 -0.0139 0.0304 1.0000
15.750 1.5305 0.05213 0.04572 -0.0139 0.0302 1.0000
16.000 1.5292 0.05527 0.04895 -0.0142 0.0300 1.0000
16.250 1.5269 0.05863 0.05242 -0.0146 0.0299 1.0000
16.500 1.5235 0.06224 0.05613 -0.0153 0.0297 1.0000
16.750 1.5191 0.06606 0.06005 -0.0161 0.0296 1.0000
17.000 1.5138 0.07013 0.06422 -0.0172 0.0295 1.0000
17.250 1.5075 0.07444 0.06863 -0.0184 0.0294 1.0000
17.500 1.5000 0.07897 0.07326 -0.0199 0.0293 1.0000
17.750 1.4918 0.08371 0.07810 -0.0215 0.0292 1.0000
18.000 1.4832 0.08860 0.08310 -0.0232 0.0291 1.0000
18.250 1.4741 0.09362 0.08822 -0.0251 0.0290 1.0000
18.500 1.4647 0.09872 0.09341 -0.0271 0.0289 1.0000
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