GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Reynolds number: 200,000 Max Cl/Cd: 60.14 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe344-il-200000-n5.txt Download as CSV file: xf-goe344-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 344 (PFALZ 71) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5320 0.09733 0.09353 -0.0121 1.0000 0.0224
-9.250 -0.5381 0.09190 0.08813 -0.0147 1.0000 0.0226
-9.000 -0.5435 0.08751 0.08380 -0.0164 1.0000 0.0229
-8.750 -0.5483 0.08403 0.08037 -0.0176 1.0000 0.0231
-8.500 -0.5490 0.08080 0.07716 -0.0190 1.0000 0.0234
-8.250 -0.5455 0.07776 0.07413 -0.0205 1.0000 0.0239
-8.000 -0.5407 0.07470 0.07107 -0.0219 1.0000 0.0246
-7.750 -0.5365 0.07082 0.06718 -0.0239 1.0000 0.0255
-7.500 -0.5335 0.06541 0.06171 -0.0268 1.0000 0.0265
-7.000 -0.5552 0.03086 0.02548 -0.0386 1.0000 0.0301
-6.750 -0.5356 0.02991 0.02449 -0.0377 1.0000 0.0312
-6.500 -0.5161 0.02842 0.02279 -0.0369 1.0000 0.0324
-6.250 -0.4972 0.02613 0.02012 -0.0359 1.0000 0.0337
-6.000 -0.4768 0.02436 0.01801 -0.0350 1.0000 0.0353
-5.750 -0.4556 0.02265 0.01590 -0.0340 1.0000 0.0369
-5.500 -0.4335 0.02120 0.01410 -0.0330 1.0000 0.0377
-5.250 -0.4107 0.02001 0.01261 -0.0321 1.0000 0.0385
-5.000 -0.3880 0.01878 0.01124 -0.0313 1.0000 0.0402
-4.750 -0.3646 0.01810 0.01047 -0.0305 1.0000 0.0414
-4.500 -0.3407 0.01738 0.00963 -0.0297 1.0000 0.0424
-4.250 -0.3165 0.01672 0.00886 -0.0290 1.0000 0.0435
-4.000 -0.2921 0.01613 0.00815 -0.0282 1.0000 0.0446
-3.750 -0.2675 0.01560 0.00753 -0.0275 1.0000 0.0458
-3.500 -0.2428 0.01519 0.00704 -0.0269 1.0000 0.0473
-3.250 -0.2164 0.01478 0.00656 -0.0266 0.9996 0.0490
-3.000 -0.1819 0.01425 0.00605 -0.0280 0.9970 0.0515
-2.750 -0.1463 0.01389 0.00567 -0.0297 0.9944 0.0544
-2.500 -0.1100 0.01352 0.00526 -0.0315 0.9898 0.0585
-2.250 -0.0700 0.01311 0.00491 -0.0341 0.9850 0.0658
-2.000 -0.0322 0.01273 0.00458 -0.0361 0.9776 0.0781
-1.750 0.0042 0.01242 0.00435 -0.0379 0.9694 0.0955
-1.500 0.0410 0.01217 0.00415 -0.0396 0.9602 0.1144
-1.250 0.0776 0.01192 0.00394 -0.0413 0.9494 0.1297
-1.000 0.1132 0.01167 0.00373 -0.0428 0.9379 0.1445
-0.750 0.1479 0.01141 0.00355 -0.0441 0.9253 0.1620
-0.500 0.1845 0.01111 0.00333 -0.0458 0.9114 0.1801
-0.250 0.2224 0.01082 0.00312 -0.0477 0.8937 0.1998
0.000 0.2572 0.01057 0.00296 -0.0489 0.8678 0.2276
0.250 0.2906 0.01032 0.00282 -0.0498 0.8280 0.2789
0.500 0.3208 0.01009 0.00264 -0.0499 0.7676 0.3551
1.000 0.4137 0.00924 0.00280 -0.0566 0.6603 1.0000
1.250 0.4375 0.00949 0.00281 -0.0555 0.6193 1.0000
1.500 0.4611 0.00973 0.00284 -0.0544 0.5795 1.0000
1.750 0.4846 0.00999 0.00289 -0.0534 0.5430 1.0000
2.000 0.5081 0.01024 0.00297 -0.0524 0.5076 1.0000
2.250 0.5317 0.01050 0.00305 -0.0514 0.4723 1.0000
2.500 0.5552 0.01077 0.00316 -0.0504 0.4373 1.0000
2.750 0.5786 0.01106 0.00328 -0.0494 0.4037 1.0000
3.000 0.6022 0.01135 0.00343 -0.0485 0.3761 1.0000
3.250 0.6260 0.01164 0.00360 -0.0477 0.3551 1.0000
3.500 0.6500 0.01191 0.00380 -0.0468 0.3376 1.0000
3.750 0.6741 0.01219 0.00401 -0.0460 0.3224 1.0000
4.000 0.6981 0.01249 0.00423 -0.0453 0.3047 1.0000
4.250 0.7220 0.01281 0.00446 -0.0445 0.2849 1.0000
4.500 0.7462 0.01309 0.00469 -0.0438 0.2685 1.0000
4.750 0.7709 0.01334 0.00493 -0.0431 0.2555 1.0000
5.000 0.7955 0.01360 0.00519 -0.0424 0.2423 1.0000
5.250 0.8201 0.01388 0.00547 -0.0418 0.2281 1.0000
5.500 0.8447 0.01417 0.00575 -0.0412 0.2141 1.0000
5.750 0.8691 0.01448 0.00606 -0.0405 0.1981 1.0000
6.000 0.8931 0.01485 0.00639 -0.0398 0.1788 1.0000
6.250 0.9170 0.01525 0.00675 -0.0392 0.1560 1.0000
6.500 0.9401 0.01576 0.00717 -0.0384 0.1322 1.0000
6.750 0.9628 0.01635 0.00768 -0.0376 0.1103 1.0000
7.000 0.9851 0.01699 0.00828 -0.0367 0.0949 1.0000
7.250 1.0076 0.01760 0.00889 -0.0359 0.0843 1.0000
7.500 1.0300 0.01822 0.00955 -0.0350 0.0769 1.0000
7.750 1.0517 0.01889 0.01024 -0.0340 0.0707 1.0000
8.000 1.0736 0.01952 0.01094 -0.0331 0.0650 1.0000
8.250 1.0953 0.02016 0.01164 -0.0322 0.0591 1.0000
8.500 1.1159 0.02090 0.01244 -0.0312 0.0546 1.0000
8.750 1.1377 0.02149 0.01315 -0.0303 0.0502 1.0000
9.000 1.1575 0.02228 0.01397 -0.0292 0.0458 1.0000
9.250 1.1780 0.02298 0.01480 -0.0281 0.0420 1.0000
9.500 1.1982 0.02367 0.01561 -0.0271 0.0377 1.0000
9.750 1.2167 0.02453 0.01655 -0.0258 0.0338 1.0000
10.000 1.2355 0.02533 0.01746 -0.0246 0.0301 1.0000
10.250 1.2514 0.02639 0.01858 -0.0230 0.0272 1.0000
10.500 1.2679 0.02735 0.01970 -0.0215 0.0243 1.0000
10.750 1.2824 0.02842 0.02082 -0.0199 0.0221 1.0000
11.000 1.2945 0.02967 0.02224 -0.0179 0.0204 1.0000
11.250 1.3054 0.03096 0.02369 -0.0157 0.0191 1.0000
11.500 1.3141 0.03229 0.02517 -0.0134 0.0181 1.0000
11.750 1.3190 0.03366 0.02666 -0.0106 0.0172 1.0000
12.000 1.3194 0.03534 0.02845 -0.0075 0.0165 1.0000
12.250 1.3182 0.03729 0.03055 -0.0046 0.0159 1.0000
12.500 1.3187 0.03926 0.03272 -0.0024 0.0154 1.0000
12.750 1.3174 0.04152 0.03517 -0.0006 0.0148 1.0000
13.000 1.3146 0.04411 0.03795 0.0007 0.0143 1.0000
13.250 1.3101 0.04713 0.04115 0.0013 0.0139 1.0000
13.500 1.3038 0.05071 0.04492 0.0010 0.0136 1.0000
13.750 1.2958 0.05496 0.04936 -0.0002 0.0134 1.0000
14.000 1.2862 0.05986 0.05445 -0.0023 0.0132 1.0000
14.250 1.2749 0.06542 0.06019 -0.0050 0.0131 1.0000
14.500 1.2614 0.07160 0.06658 -0.0083 0.0130 1.0000
14.750 1.2461 0.07833 0.07348 -0.0120 0.0129 1.0000
15.000 1.2290 0.08551 0.08081 -0.0158 0.0129 1.0000
15.250 1.2103 0.09314 0.08861 -0.0199 0.0129 1.0000
15.500 1.1901 0.10117 0.09680 -0.0241 0.0129 1.0000
15.750 1.1685 0.10969 0.10547 -0.0286 0.0130 1.0000
16.000 1.1452 0.11897 0.11492 -0.0335 0.0131 1.0000
16.250 1.1182 0.12960 0.12572 -0.0393 0.0132 1.0000
16.500 1.0781 0.14446 0.14079 -0.0475 0.0136 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 344 (PFALZ 71) AIRFOIL (goe344-il)