PW75 (pw75-pw) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: PW75 (pw75-pw) Reynolds number: 200,000 Max Cl/Cd: 56.97 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pw75-pw-200000.txt Download as CSV file: xf-pw75-pw-200000.csv |
XFOIL Version 6.96
Calculated polar for: PW75
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6329 0.11482 0.11161 0.0337 1.0000 0.0359
-9.500 -0.6294 0.11100 0.10780 0.0323 1.0000 0.0370
-9.250 -0.6275 0.10678 0.10359 0.0302 1.0000 0.0377
-9.000 -0.6263 0.10241 0.09924 0.0279 1.0000 0.0384
-8.750 -0.6258 0.09790 0.09475 0.0252 1.0000 0.0391
-8.500 -0.6259 0.09320 0.09008 0.0220 1.0000 0.0398
-8.250 -0.6272 0.08815 0.08506 0.0179 1.0000 0.0404
-8.000 -0.6303 0.08239 0.07934 0.0118 1.0000 0.0409
-7.750 -0.6310 0.07615 0.07305 0.0053 1.0000 0.0416
-7.500 -0.6283 0.06955 0.06633 -0.0006 1.0000 0.0429
-7.250 -0.6226 0.06396 0.06022 -0.0060 1.0000 0.0451
-7.000 -0.6133 0.05987 0.05584 -0.0069 1.0000 0.0453
-6.750 -0.6120 0.05138 0.04726 -0.0083 1.0000 0.0466
-6.500 -0.5957 0.04830 0.04417 -0.0084 1.0000 0.0478
-6.250 -0.5761 0.04737 0.04332 -0.0082 1.0000 0.0525
-5.750 -0.5406 0.04197 0.03753 -0.0088 1.0000 0.0667
-5.000 -0.4713 0.02999 0.02368 -0.0061 1.0000 0.0449
-4.750 -0.4460 0.02537 0.01844 -0.0047 1.0000 0.0327
-4.500 -0.4224 0.02141 0.01417 -0.0041 1.0000 0.0299
-4.250 -0.3962 0.01931 0.01181 -0.0035 1.0000 0.0282
-4.000 -0.3694 0.01763 0.00994 -0.0030 1.0000 0.0269
-3.750 -0.3431 0.01624 0.00843 -0.0025 1.0000 0.0259
-3.500 -0.3181 0.01513 0.00727 -0.0019 1.0000 0.0252
-3.250 -0.2961 0.01428 0.00640 -0.0010 1.0000 0.0249
-3.000 -0.2603 0.01347 0.00553 -0.0028 0.9882 0.0248
-2.750 -0.2181 0.01282 0.00479 -0.0057 0.9694 0.0254
-2.500 -0.1816 0.01240 0.00425 -0.0071 0.9469 0.0268
-2.250 -0.1533 0.01212 0.00387 -0.0066 0.9223 0.0296
-2.000 -0.1306 0.01177 0.00354 -0.0049 0.8982 0.0482
-1.750 -0.1123 0.01075 0.00326 -0.0030 0.8757 0.2310
-1.500 -0.0993 0.00919 0.00311 -0.0003 0.8539 0.5715
-1.250 -0.0838 0.00852 0.00310 0.0034 0.8346 0.7681
-1.000 -0.0556 0.00848 0.00330 0.0051 0.8145 0.9000
-0.750 -0.0186 0.00864 0.00336 0.0043 0.7953 0.9516
-0.500 0.0578 0.00879 0.00337 -0.0049 0.7730 1.0000
-0.250 0.0830 0.00882 0.00326 -0.0043 0.7519 1.0000
0.000 0.1084 0.00887 0.00316 -0.0037 0.7317 1.0000
0.250 0.1342 0.00891 0.00306 -0.0032 0.7110 1.0000
0.500 0.1598 0.00898 0.00298 -0.0026 0.6917 1.0000
0.750 0.1858 0.00904 0.00294 -0.0022 0.6711 1.0000
1.000 0.2116 0.00914 0.00290 -0.0017 0.6522 1.0000
1.250 0.2377 0.00922 0.00289 -0.0013 0.6320 1.0000
1.500 0.2636 0.00934 0.00288 -0.0008 0.6132 1.0000
1.750 0.2896 0.00944 0.00290 -0.0004 0.5934 1.0000
2.000 0.3155 0.00958 0.00292 0.0000 0.5746 1.0000
2.250 0.3416 0.00971 0.00300 0.0004 0.5552 1.0000
2.500 0.3675 0.00986 0.00305 0.0008 0.5363 1.0000
2.750 0.3934 0.01002 0.00312 0.0012 0.5173 1.0000
3.000 0.4194 0.01018 0.00321 0.0016 0.4982 1.0000
3.250 0.4451 0.01037 0.00331 0.0021 0.4799 1.0000
3.500 0.4710 0.01055 0.00344 0.0024 0.4607 1.0000
3.750 0.4967 0.01077 0.00357 0.0028 0.4427 1.0000
4.000 0.5226 0.01098 0.00381 0.0032 0.4239 1.0000
4.250 0.5483 0.01120 0.00398 0.0036 0.4058 1.0000
4.500 0.5740 0.01146 0.00416 0.0040 0.3886 1.0000
4.750 0.5999 0.01170 0.00438 0.0043 0.3703 1.0000
5.000 0.6256 0.01197 0.00460 0.0046 0.3529 1.0000
5.250 0.6512 0.01228 0.00483 0.0049 0.3362 1.0000
5.500 0.6770 0.01255 0.00511 0.0052 0.3182 1.0000
5.750 0.7026 0.01286 0.00539 0.0055 0.3008 1.0000
6.000 0.7280 0.01322 0.00569 0.0058 0.2841 1.0000
6.250 0.7537 0.01356 0.00604 0.0060 0.2669 1.0000
6.500 0.7791 0.01393 0.00641 0.0063 0.2499 1.0000
6.750 0.8041 0.01434 0.00675 0.0065 0.2315 1.0000
7.000 0.8295 0.01466 0.00730 0.0067 0.2103 1.0000
7.250 0.8545 0.01500 0.00759 0.0068 0.1844 1.0000
7.500 0.8789 0.01545 0.00792 0.0068 0.1550 1.0000
7.750 0.9029 0.01604 0.00837 0.0069 0.1278 1.0000
8.000 0.9271 0.01663 0.00893 0.0071 0.1093 1.0000
8.250 0.9510 0.01726 0.00955 0.0073 0.0941 1.0000
8.500 0.9745 0.01795 0.01024 0.0076 0.0802 1.0000
8.750 0.9975 0.01869 0.01100 0.0078 0.0679 1.0000
9.000 1.0201 0.01951 0.01185 0.0081 0.0579 1.0000
9.250 1.0413 0.02050 0.01284 0.0085 0.0495 1.0000
9.500 1.0635 0.02130 0.01381 0.0089 0.0439 1.0000
9.750 1.0847 0.02217 0.01465 0.0091 0.0345 1.0000
10.000 1.1045 0.02321 0.01581 0.0095 0.0271 1.0000
10.250 1.1244 0.02421 0.01700 0.0100 0.0241 1.0000
10.500 1.1431 0.02533 0.01827 0.0104 0.0196 1.0000
10.750 1.1563 0.02712 0.02022 0.0112 0.0150 1.0000
11.000 1.1693 0.02881 0.02215 0.0120 0.0115 1.0000
11.250 1.1778 0.03086 0.02436 0.0128 0.0096 1.0000
11.500 1.1797 0.03332 0.02702 0.0136 0.0086 1.0000
11.750 1.1737 0.03638 0.03029 0.0141 0.0081 1.0000
12.000 1.1656 0.04020 0.03432 0.0132 0.0078 1.0000
12.250 1.1559 0.04468 0.03902 0.0114 0.0076 1.0000
12.500 1.1458 0.04954 0.04408 0.0091 0.0075 1.0000
12.750 1.1343 0.05481 0.04955 0.0065 0.0074 1.0000
13.250 1.1114 0.06583 0.06089 0.0009 0.0074 1.0000
13.500 1.0987 0.07172 0.06695 -0.0022 0.0074 1.0000
13.750 1.0847 0.07799 0.07338 -0.0054 0.0074 1.0000
14.250 1.0567 0.09103 0.08675 -0.0124 0.0074 1.0000
14.500 1.0433 0.09788 0.09373 -0.0160 0.0075 1.0000
14.750 1.0307 0.10480 0.10077 -0.0198 0.0076 1.0000
15.000 1.0176 0.11207 0.10816 -0.0236 0.0076 1.0000
15.250 1.0046 0.11956 0.11576 -0.0276 0.0078 1.0000
15.500 0.9909 0.12745 0.12376 -0.0318 0.0079 1.0000
15.750 0.9770 0.13573 0.13214 -0.0361 0.0081 1.0000
16.000 0.9595 0.14538 0.14192 -0.0411 0.0084 1.0000
16.250 0.8713 0.18043 0.17692 -0.0566 0.0117 1.0000
16.500 0.8665 0.18891 0.18535 -0.0604 0.0120 1.0000
16.750 0.8664 0.19585 0.19226 -0.0636 0.0121 1.0000
17.000 0.8685 0.20198 0.19836 -0.0665 0.0123 1.0000
17.250 0.8722 0.20757 0.20393 -0.0692 0.0125 1.0000
17.500 0.8768 0.21274 0.20908 -0.0717 0.0128 1.0000
17.750 0.8821 0.21762 0.21394 -0.0742 0.0131 1.0000
18.000 0.8879 0.22222 0.21853 -0.0766 0.0136 1.0000
18.250 0.8942 0.22660 0.22290 -0.0788 0.0140 1.0000
18.500 0.9003 0.23085 0.22715 -0.0807 0.0148 1.0000
18.750 0.6328 0.20371 0.20037 -0.0447 0.0213 1.0000
19.250 0.6448 0.21113 0.20781 -0.0447 0.0260 1.0000
19.500 0.6470 0.21457 0.21125 -0.0460 0.0260 1.0000
19.750 0.6493 0.21791 0.21460 -0.0472 0.0259 1.0000
20.000 0.6515 0.22121 0.21790 -0.0485 0.0259 1.0000
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