GOE 746 AIRFOIL (goe746-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 746 AIRFOIL (goe746-il) Reynolds number: 200,000 Max Cl/Cd: 73.84 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe746-il-200000-n5.txt Download as CSV file: xf-goe746-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 746 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3873 0.09822 0.09401 0.0130 0.5946 0.0242
-7.750 -0.3874 0.09503 0.09083 0.0106 0.5909 0.0243
-7.500 -0.3873 0.09197 0.08775 0.0086 0.5876 0.0243
-7.250 -0.3820 0.08837 0.08414 0.0057 0.5837 0.0244
-7.000 -0.3297 0.07483 0.07079 0.0039 0.5716 0.0245
-6.750 -0.3644 0.08060 0.07627 0.0000 0.5763 0.0245
-6.250 -0.3433 0.07202 0.06757 -0.0042 0.5695 0.0250
-6.000 -0.3320 0.06959 0.06513 -0.0032 0.5651 0.0258
-5.750 -0.3174 0.06649 0.06196 -0.0045 0.5617 0.0267
-5.500 -0.3009 0.06313 0.05849 -0.0064 0.5587 0.0276
-5.250 -0.2717 0.05933 0.05441 -0.0110 0.5559 0.0315
-5.000 -0.2478 0.05529 0.05012 -0.0130 0.5525 0.0319
-4.750 -0.2306 0.05020 0.04484 -0.0140 0.5494 0.0323
-4.500 -0.2160 0.04720 0.04180 -0.0140 0.5459 0.0332
-4.250 -0.1966 0.04485 0.03932 -0.0140 0.5429 0.0341
-4.000 -0.1745 0.04213 0.03644 -0.0143 0.5398 0.0351
-3.500 -0.1245 0.03657 0.03032 -0.0145 0.5335 0.0401
-3.250 -0.1025 0.03318 0.02666 -0.0140 0.5306 0.0363
-3.000 -0.0778 0.03035 0.02344 -0.0134 0.5279 0.0360
-2.750 -0.0526 0.02838 0.02117 -0.0128 0.5249 0.0375
-2.500 -0.0269 0.02596 0.01838 -0.0121 0.5217 0.0364
-2.250 -0.0006 0.02404 0.01611 -0.0114 0.5187 0.0360
-2.000 0.0259 0.02264 0.01439 -0.0109 0.5158 0.0366
-1.750 0.0528 0.02157 0.01303 -0.0104 0.5130 0.0380
-1.500 0.0801 0.02040 0.01158 -0.0099 0.5102 0.0378
-1.250 0.1079 0.01938 0.01033 -0.0096 0.5068 0.0377
-1.000 0.1359 0.01853 0.00929 -0.0093 0.5036 0.0379
-0.750 0.1638 0.01782 0.00841 -0.0091 0.5008 0.0381
-0.500 0.1917 0.01722 0.00765 -0.0088 0.4981 0.0385
-0.250 0.2194 0.01680 0.00710 -0.0086 0.4954 0.0397
0.000 0.2474 0.01643 0.00670 -0.0085 0.4919 0.0407
0.250 0.2751 0.01599 0.00624 -0.0083 0.4887 0.0409
0.500 0.3023 0.01560 0.00582 -0.0081 0.4858 0.0411
0.750 0.3293 0.01528 0.00547 -0.0078 0.4830 0.0413
1.000 0.3560 0.01503 0.00519 -0.0075 0.4804 0.0416
1.250 0.3827 0.01477 0.00498 -0.0072 0.4770 0.0423
1.500 0.4094 0.01457 0.00479 -0.0070 0.4736 0.0433
1.750 0.4362 0.01445 0.00464 -0.0067 0.4704 0.0449
2.000 0.4632 0.01438 0.00453 -0.0065 0.4676 0.0467
2.250 0.4902 0.01436 0.00448 -0.0063 0.4647 0.0511
2.500 0.5174 0.01432 0.00452 -0.0061 0.4607 0.0569
2.750 0.5443 0.01427 0.00452 -0.0059 0.4569 0.0737
3.250 0.6821 0.01246 0.00473 -0.0233 0.4453 1.0000
3.500 0.7079 0.01255 0.00479 -0.0230 0.4409 1.0000
3.750 0.7335 0.01264 0.00483 -0.0225 0.4374 1.0000
4.000 0.7592 0.01277 0.00495 -0.0222 0.4332 1.0000
4.250 0.7850 0.01290 0.00511 -0.0219 0.4286 1.0000
4.500 0.8105 0.01301 0.00522 -0.0215 0.4244 1.0000
4.750 0.8360 0.01313 0.00530 -0.0211 0.4208 1.0000
5.000 0.8616 0.01329 0.00554 -0.0208 0.4156 1.0000
5.250 0.8870 0.01342 0.00572 -0.0205 0.4107 1.0000
5.500 0.9122 0.01354 0.00581 -0.0201 0.4066 1.0000
5.750 0.9376 0.01373 0.00611 -0.0198 0.4011 1.0000
6.000 0.9628 0.01389 0.00631 -0.0195 0.3960 1.0000
6.250 0.9878 0.01405 0.00649 -0.0191 0.3912 1.0000
6.500 1.0129 0.01425 0.00681 -0.0188 0.3846 1.0000
6.750 1.0377 0.01442 0.00701 -0.0184 0.3788 1.0000
7.000 1.0624 0.01461 0.00730 -0.0181 0.3693 1.0000
7.250 1.0866 0.01479 0.00751 -0.0177 0.3564 1.0000
7.500 1.1105 0.01504 0.00777 -0.0173 0.3415 1.0000
7.750 1.1332 0.01538 0.00806 -0.0169 0.3202 1.0000
8.000 1.1552 0.01587 0.00852 -0.0165 0.2959 1.0000
8.250 1.1752 0.01657 0.00912 -0.0160 0.2682 1.0000
8.500 1.1932 0.01748 0.00992 -0.0155 0.2396 1.0000
8.750 1.2061 0.01891 0.01112 -0.0148 0.2000 1.0000
9.000 1.2122 0.02087 0.01278 -0.0139 0.1481 1.0000
9.250 1.1960 0.02456 0.01595 -0.0124 0.0751 1.0000
9.500 1.1764 0.02793 0.01917 -0.0107 0.0366 1.0000
9.750 1.1671 0.03069 0.02193 -0.0095 0.0278 1.0000
10.000 1.1663 0.03297 0.02429 -0.0088 0.0244 1.0000
10.250 1.1668 0.03524 0.02667 -0.0083 0.0226 1.0000
10.500 1.1665 0.03768 0.02921 -0.0079 0.0212 1.0000
10.750 1.1639 0.04041 0.03204 -0.0077 0.0197 1.0000
11.000 1.1591 0.04347 0.03522 -0.0075 0.0184 1.0000
11.250 1.1588 0.04608 0.03794 -0.0075 0.0177 1.0000
11.500 1.1577 0.04881 0.04080 -0.0074 0.0171 1.0000
11.750 1.1548 0.05182 0.04393 -0.0076 0.0167 1.0000
12.000 1.1512 0.05499 0.04722 -0.0078 0.0162 1.0000
12.250 1.1476 0.05831 0.05068 -0.0082 0.0158 1.0000
12.500 1.1427 0.06190 0.05439 -0.0087 0.0152 1.0000
12.750 1.1385 0.06551 0.05811 -0.0094 0.0149 1.0000
13.000 1.1338 0.06926 0.06196 -0.0101 0.0144 1.0000
13.250 1.1298 0.07300 0.06580 -0.0109 0.0143 1.0000
13.500 1.1241 0.07704 0.06993 -0.0118 0.0139 1.0000
13.750 1.1185 0.08109 0.07405 -0.0127 0.0134 1.0000
14.000 1.1109 0.08538 0.07839 -0.0137 0.0128 1.0000
14.250 1.1078 0.08895 0.08199 -0.0143 0.0124 1.0000
14.500 1.1102 0.09185 0.08496 -0.0148 0.0123 1.0000
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Polar data table (+)
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