GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.76 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe244-il-1000000-n5.txt Download as CSV file: xf-goe244-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 244 (MVA PR.4) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.2870 0.08988 0.08688 -0.1238 0.7167 0.0190
-10.500 0.2946 0.08707 0.08406 -0.1248 0.7113 0.0192
-10.250 0.3020 0.08416 0.08112 -0.1259 0.7049 0.0193
-10.000 0.3090 0.08133 0.07824 -0.1269 0.6963 0.0194
-9.500 0.2612 0.08729 0.08413 -0.1265 0.7083 0.0192
-9.000 0.0875 0.03626 0.03268 -0.1735 0.7059 0.0210
-8.750 0.1220 0.02784 0.02395 -0.1948 0.6983 0.0211
-8.500 0.1687 0.02387 0.01976 -0.2080 0.6916 0.0212
-8.250 0.2169 0.02117 0.01686 -0.2184 0.6825 0.0213
-8.000 0.2638 0.01923 0.01472 -0.2267 0.6740 0.0214
-7.750 0.3042 0.01800 0.01334 -0.2316 0.6661 0.0216
-7.500 0.3406 0.01712 0.01229 -0.2350 0.6577 0.0217
-7.250 0.3766 0.01634 0.01139 -0.2378 0.6497 0.0218
-7.000 0.4108 0.01570 0.01061 -0.2400 0.6410 0.0220
-6.750 0.4448 0.01512 0.00992 -0.2419 0.6339 0.0221
-6.500 0.4782 0.01460 0.00929 -0.2436 0.6259 0.0223
-6.250 0.5107 0.01417 0.00874 -0.2450 0.6178 0.0224
-6.000 0.5435 0.01375 0.00823 -0.2464 0.6103 0.0226
-5.750 0.5754 0.01340 0.00778 -0.2474 0.6023 0.0227
-5.500 0.6073 0.01308 0.00737 -0.2485 0.5954 0.0229
-5.250 0.6389 0.01279 0.00700 -0.2494 0.5867 0.0230
-5.000 0.6698 0.01257 0.00669 -0.2502 0.5780 0.0231
-4.750 0.7007 0.01236 0.00640 -0.2509 0.5673 0.0233
-4.500 0.7308 0.01222 0.00616 -0.2515 0.5548 0.0234
-4.250 0.7598 0.01215 0.00597 -0.2518 0.5379 0.0235
-4.000 0.7878 0.01215 0.00584 -0.2520 0.5152 0.0237
-3.750 0.8140 0.01229 0.00580 -0.2518 0.4870 0.0238
-3.500 0.8407 0.01238 0.00573 -0.2517 0.4623 0.0240
-3.250 0.8688 0.01237 0.00560 -0.2520 0.4432 0.0243
-3.000 0.8963 0.01243 0.00555 -0.2520 0.4284 0.0245
-2.750 0.9247 0.01243 0.00549 -0.2522 0.4179 0.0248
-2.500 0.9523 0.01249 0.00547 -0.2523 0.4083 0.0250
-2.250 0.9808 0.01250 0.00543 -0.2524 0.4013 0.0253
-2.000 1.0083 0.01256 0.00543 -0.2524 0.3940 0.0256
-1.750 1.0359 0.01261 0.00543 -0.2524 0.3879 0.0260
-1.500 1.0639 0.01264 0.00543 -0.2524 0.3826 0.0263
-1.250 1.0908 0.01272 0.00546 -0.2523 0.3766 0.0266
-1.000 1.1167 0.01284 0.00552 -0.2520 0.3702 0.0270
-0.750 1.1438 0.01290 0.00556 -0.2518 0.3663 0.0272
-0.500 1.1704 0.01298 0.00561 -0.2516 0.3621 0.0276
-0.250 1.1965 0.01306 0.00566 -0.2513 0.3578 0.0281
0.000 1.2209 0.01320 0.00576 -0.2507 0.3534 0.0287
0.250 1.2437 0.01334 0.00588 -0.2498 0.3497 0.0293
0.500 1.2670 0.01345 0.00598 -0.2489 0.3473 0.0302
0.750 1.2898 0.01358 0.00611 -0.2480 0.3445 0.0311
1.000 1.3137 0.01374 0.00626 -0.2473 0.3415 0.0324
1.250 1.3378 0.01394 0.00644 -0.2467 0.3384 0.0340
1.500 1.3614 0.01417 0.00665 -0.2460 0.3351 0.0374
1.750 1.3856 0.01437 0.00690 -0.2456 0.3317 0.0729
2.000 1.4099 0.01457 0.00711 -0.2450 0.3298 0.0825
2.250 1.4376 0.01460 0.00734 -0.2454 0.3281 0.1836
2.500 1.4616 0.01480 0.00760 -0.2449 0.3261 0.2114
2.750 1.4846 0.01505 0.00788 -0.2442 0.3240 0.2274
3.000 1.5072 0.01533 0.00818 -0.2434 0.3218 0.2428
3.250 1.5292 0.01563 0.00852 -0.2426 0.3195 0.2607
3.500 1.5505 0.01598 0.00889 -0.2417 0.3170 0.2809
3.750 1.5712 0.01636 0.00930 -0.2407 0.3134 0.3055
4.000 1.5937 0.01665 0.00965 -0.2401 0.3110 0.3376
4.250 1.6158 0.01697 0.01003 -0.2394 0.3085 0.3704
4.500 1.6368 0.01734 0.01046 -0.2385 0.3058 0.4007
4.750 1.6572 0.01775 0.01090 -0.2375 0.3032 0.4205
5.000 1.6766 0.01822 0.01137 -0.2364 0.3005 0.4348
5.250 1.6948 0.01875 0.01191 -0.2351 0.2976 0.4455
5.500 1.7128 0.01931 0.01247 -0.2338 0.2946 0.4546
5.750 1.7334 0.01973 0.01292 -0.2329 0.2935 0.4621
6.000 1.7533 0.02019 0.01342 -0.2320 0.2925 0.4697
6.250 1.7725 0.02069 0.01395 -0.2309 0.2911 0.4751
6.500 1.7916 0.02120 0.01448 -0.2299 0.2895 0.4799
6.750 1.8103 0.02175 0.01505 -0.2288 0.2875 0.4849
7.000 1.8276 0.02238 0.01570 -0.2276 0.2854 0.4892
7.250 1.8447 0.02304 0.01637 -0.2264 0.2833 0.4930
7.500 1.8615 0.02372 0.01706 -0.2252 0.2814 0.4963
7.750 1.8770 0.02450 0.01785 -0.2238 0.2793 0.4999
8.000 1.8928 0.02525 0.01865 -0.2225 0.2774 0.5066
8.250 1.9109 0.02586 0.01930 -0.2216 0.2764 0.5157
8.500 1.9280 0.02655 0.02005 -0.2205 0.2749 0.5247
8.750 1.9445 0.02729 0.02083 -0.2194 0.2729 0.5317
9.000 1.9607 0.02806 0.02163 -0.2183 0.2708 0.5362
9.250 1.9757 0.02893 0.02253 -0.2170 0.2683 0.5407
9.500 1.9883 0.02999 0.02359 -0.2156 0.2647 0.5452
9.750 2.0013 0.03102 0.02464 -0.2142 0.2606 0.5500
10.000 2.0162 0.03195 0.02560 -0.2131 0.2571 0.5550
10.250 2.0291 0.03302 0.02671 -0.2118 0.2528 0.5612
10.500 2.0400 0.03428 0.02796 -0.2103 0.2479 0.5689
11.000 2.0590 0.03705 0.03075 -0.2073 0.2340 0.5874
11.250 2.0658 0.03870 0.03239 -0.2056 0.2251 0.5980
11.500 2.0673 0.04082 0.03448 -0.2035 0.2119 0.6111
11.750 2.0553 0.04418 0.03772 -0.2003 0.1892 0.6233
12.000 2.0450 0.04748 0.04096 -0.1974 0.1724 0.6385
12.250 2.0398 0.05042 0.04389 -0.1952 0.1612 0.6597
12.500 2.0387 0.05307 0.04659 -0.1934 0.1540 0.6903
12.750 2.0380 0.05572 0.04933 -0.1918 0.1476 0.7451
13.000 2.0407 0.05772 0.05157 -0.1903 0.1438 1.0000
13.250 2.0411 0.06032 0.05419 -0.1888 0.1399 1.0000
13.500 2.0411 0.06300 0.05690 -0.1874 0.1359 1.0000
13.750 2.0441 0.06541 0.05935 -0.1863 0.1335 1.0000
14.000 2.0451 0.06803 0.06200 -0.1852 0.1300 1.0000
14.250 2.0421 0.07114 0.06515 -0.1839 0.1266 1.0000
14.500 2.0398 0.07417 0.06821 -0.1827 0.1230 1.0000
14.750 2.0391 0.07710 0.07120 -0.1818 0.1207 1.0000
15.000 2.0382 0.08005 0.07419 -0.1808 0.1180 1.0000
15.250 2.0330 0.08358 0.07777 -0.1799 0.1151 1.0000
15.500 2.0253 0.08742 0.08166 -0.1790 0.1121 1.0000
15.750 2.0228 0.09063 0.08493 -0.1782 0.1098 1.0000
16.000 2.0169 0.09434 0.08870 -0.1776 0.1075 1.0000
16.250 2.0087 0.09836 0.09278 -0.1770 0.1045 1.0000
16.500 1.9976 0.10282 0.09728 -0.1766 0.1014 1.0000
16.750 1.9880 0.10714 0.10167 -0.1763 0.0987 1.0000
17.000 1.9766 0.11172 0.10633 -0.1762 0.0954 1.0000
17.250 1.9607 0.11701 0.11167 -0.1763 0.0917 1.0000
17.500 1.9462 0.12218 0.11689 -0.1766 0.0877 1.0000
17.750 1.9280 0.12795 0.12272 -0.1773 0.0826 1.0000
18.000 1.9021 0.13493 0.12972 -0.1784 0.0744 1.0000
18.250 1.8707 0.14287 0.13766 -0.1802 0.0643 1.0000
18.500 1.8401 0.15088 0.14568 -0.1824 0.0530 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 244 (MVA PR.4) AIRFOIL (goe244-il)