WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Reynolds number: 500,000 Max Cl/Cd: 123.11 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx72150a-il-500000.txt Download as CSV file: xf-fx72150a-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 72-MS-150A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.2072 0.09097 0.08706 -0.1409 0.7171 0.0188
-9.500 0.2092 0.08844 0.08449 -0.1428 0.7124 0.0191
-9.250 0.2100 0.08566 0.08174 -0.1450 0.7075 0.0192
-9.000 0.2189 0.08307 0.07914 -0.1455 0.7026 0.0193
-8.750 0.2325 0.08100 0.07701 -0.1453 0.6976 0.0195
-8.500 0.2428 0.07894 0.07496 -0.1458 0.6930 0.0197
-8.250 0.2521 0.07695 0.07296 -0.1463 0.6884 0.0201
-8.000 0.2598 0.07483 0.07082 -0.1471 0.6838 0.0206
-7.750 0.2673 0.07271 0.06866 -0.1479 0.6795 0.0207
-7.500 0.2737 0.07036 0.06634 -0.1488 0.6755 0.0216
-7.250 0.2714 0.06717 0.06318 -0.1513 0.6714 0.0224
-7.000 0.2700 0.06394 0.05996 -0.1526 0.6674 0.0226
-6.750 0.2786 0.06219 0.05817 -0.1523 0.6635 0.0227
-6.500 0.2868 0.06060 0.05660 -0.1519 0.6598 0.0230
-6.250 0.2934 0.05889 0.05491 -0.1521 0.6559 0.0232
-6.000 0.3025 0.05682 0.05285 -0.1534 0.6521 0.0236
-5.750 0.3124 0.05441 0.05041 -0.1557 0.6486 0.0241
-5.500 0.3245 0.05145 0.04742 -0.1594 0.6452 0.0250
-5.250 0.3530 0.03991 0.03574 -0.1823 0.6422 0.0263
-5.000 0.3720 0.03838 0.03421 -0.1835 0.6388 0.0266
-4.750 0.3955 0.03607 0.03183 -0.1869 0.6355 0.0271
-4.500 0.4238 0.03309 0.02867 -0.1918 0.6325 0.0279
-4.250 0.4670 0.02737 0.02230 -0.2011 0.6295 0.0305
-4.000 0.4941 0.02585 0.02076 -0.2028 0.6268 0.0310
-3.750 0.5240 0.02431 0.01910 -0.2049 0.6240 0.0321
-3.500 0.5606 0.02188 0.01623 -0.2083 0.6212 0.0353
-3.250 0.5901 0.02074 0.01501 -0.2096 0.6185 0.0365
-3.000 0.6234 0.01939 0.01332 -0.2115 0.6159 0.0407
-2.750 0.6537 0.01862 0.01241 -0.2126 0.6132 0.0431
-2.500 0.6946 0.01468 0.00764 -0.2139 0.6112 0.0219
-2.250 0.7246 0.01391 0.00679 -0.2145 0.6088 0.0217
-2.000 0.7544 0.01338 0.00617 -0.2151 0.6062 0.0219
-1.750 0.7840 0.01304 0.00574 -0.2155 0.6037 0.0224
-1.500 0.8141 0.01261 0.00531 -0.2163 0.6012 0.0231
-1.250 0.8440 0.01242 0.00509 -0.2170 0.5988 0.0245
-1.000 0.8741 0.01236 0.00494 -0.2176 0.5962 0.0264
-0.750 0.9044 0.01212 0.00472 -0.2184 0.5942 0.0279
-0.500 0.9343 0.01195 0.00454 -0.2191 0.5922 0.0307
-0.250 0.9663 0.01154 0.00435 -0.2203 0.5900 0.1135
0.000 0.9988 0.01091 0.00452 -0.2222 0.5879 0.4644
0.250 1.0270 0.01101 0.00464 -0.2225 0.5859 0.5068
0.500 1.0551 0.01115 0.00478 -0.2226 0.5841 0.5359
0.750 1.0830 0.01134 0.00495 -0.2227 0.5823 0.5620
1.000 1.1111 0.01156 0.00514 -0.2229 0.5805 0.5804
1.250 1.1393 0.01175 0.00532 -0.2231 0.5787 0.5909
1.500 1.1669 0.01184 0.00542 -0.2233 0.5773 0.5982
1.750 1.1943 0.01195 0.00556 -0.2234 0.5757 0.6058
2.000 1.2221 0.01206 0.00566 -0.2236 0.5740 0.6117
2.250 1.2498 0.01215 0.00575 -0.2239 0.5723 0.6155
2.500 1.2775 0.01225 0.00587 -0.2241 0.5705 0.6200
2.750 1.3054 0.01237 0.00598 -0.2244 0.5690 0.6251
3.000 1.3334 0.01251 0.00609 -0.2247 0.5675 0.6300
3.250 1.3614 0.01263 0.00623 -0.2250 0.5662 0.6345
3.500 1.3896 0.01281 0.00641 -0.2254 0.5647 0.6397
3.750 1.4185 0.01308 0.00665 -0.2260 0.5631 0.6458
4.000 1.4452 0.01321 0.00685 -0.2261 0.5620 0.6518
4.250 1.4716 0.01334 0.00706 -0.2261 0.5607 0.6588
4.500 1.4980 0.01348 0.00726 -0.2262 0.5591 0.6662
4.750 1.5245 0.01362 0.00746 -0.2263 0.5575 0.6737
5.000 1.5512 0.01377 0.00766 -0.2264 0.5559 0.6826
5.250 1.5779 0.01391 0.00789 -0.2266 0.5544 0.6920
5.500 1.6049 0.01405 0.00807 -0.2268 0.5528 0.7030
5.750 1.6318 0.01414 0.00819 -0.2269 0.5504 0.7169
6.000 1.6600 0.01436 0.00842 -0.2273 0.5466 0.7342
6.250 1.6813 0.01436 0.00860 -0.2264 0.5438 0.7588
6.500 1.7023 0.01426 0.00874 -0.2254 0.5401 0.8260
6.750 1.7237 0.01417 0.00877 -0.2244 0.5365 1.0000
7.000 1.7491 0.01431 0.00890 -0.2243 0.5335 1.0000
7.250 1.7758 0.01456 0.00912 -0.2245 0.5296 1.0000
7.500 1.7940 0.01466 0.00934 -0.2230 0.5259 1.0000
7.750 1.8146 0.01480 0.00954 -0.2220 0.5221 1.0000
8.000 1.8355 0.01491 0.00969 -0.2210 0.5180 1.0000
8.250 1.8540 0.01508 0.00985 -0.2196 0.5122 1.0000
8.500 1.8632 0.01523 0.01011 -0.2164 0.5056 1.0000
8.750 1.8733 0.01545 0.01029 -0.2134 0.4985 1.0000
9.000 1.8769 0.01581 0.01077 -0.2095 0.4904 1.0000
9.250 1.8803 0.01637 0.01132 -0.2057 0.4801 1.0000
9.500 1.8819 0.01716 0.01212 -0.2019 0.4677 1.0000
9.750 1.8811 0.01821 0.01320 -0.1981 0.4492 1.0000
10.000 1.8676 0.02013 0.01502 -0.1929 0.4184 1.0000
10.250 1.8486 0.02281 0.01755 -0.1876 0.3876 1.0000
10.500 1.8201 0.02653 0.02110 -0.1819 0.3526 1.0000
10.750 1.7929 0.03060 0.02503 -0.1769 0.3240 1.0000
11.000 1.7650 0.03516 0.02947 -0.1725 0.2937 1.0000
11.250 1.7356 0.04032 0.03450 -0.1686 0.2640 1.0000
11.500 1.7077 0.04573 0.03978 -0.1653 0.2329 1.0000
11.750 1.6836 0.05104 0.04497 -0.1627 0.2050 1.0000
12.000 1.6581 0.05679 0.05057 -0.1603 0.1731 1.0000
12.250 1.6352 0.06245 0.05606 -0.1584 0.1405 1.0000
12.500 1.6138 0.06816 0.06159 -0.1568 0.1066 1.0000
12.750 1.5947 0.07376 0.06700 -0.1556 0.0732 1.0000
13.000 1.5730 0.07987 0.07288 -0.1544 0.0362 1.0000
13.250 1.5667 0.08410 0.07704 -0.1538 0.0214 1.0000
13.500 1.5684 0.08730 0.08027 -0.1534 0.0182 1.0000
13.750 1.5723 0.09019 0.08320 -0.1530 0.0168 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il)