GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Reynolds number: 500,000 Max Cl/Cd: 97.91 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe167-il-500000-n5.txt Download as CSV file: xf-goe167-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 167 (V.KARMAN PROP.2) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4025 0.10833 0.10618 -0.0104 1.0000 0.0100
-9.500 -0.4027 0.10316 0.10103 -0.0130 0.9912 0.0103
-9.250 -0.3993 0.09817 0.09603 -0.0163 0.9488 0.0106
-9.000 -0.3962 0.09569 0.09345 -0.0165 0.8904 0.0108
-8.750 -0.3936 0.09340 0.09091 -0.0165 0.8286 0.0110
-8.500 -0.3885 0.09060 0.08795 -0.0178 0.7916 0.0112
-8.250 -0.3834 0.08755 0.08478 -0.0196 0.7627 0.0115
-8.000 -0.3793 0.08432 0.08145 -0.0218 0.7367 0.0119
-7.750 -0.3734 0.08025 0.07729 -0.0259 0.7135 0.0125
-7.500 -0.3666 0.07306 0.07001 -0.0345 0.6960 0.0133
-7.250 -0.3544 0.06557 0.06239 -0.0435 0.6796 0.0140
-7.000 -0.3358 0.06279 0.05949 -0.0466 0.6596 0.0142
-6.750 -0.3159 0.05977 0.05634 -0.0500 0.6422 0.0146
-6.500 -0.2946 0.05632 0.05275 -0.0536 0.6271 0.0153
-6.250 -0.2684 0.04292 0.03886 -0.0642 0.6205 0.0179
-6.000 -0.2449 0.04093 0.03670 -0.0656 0.6069 0.0182
-5.750 -0.2205 0.03980 0.03545 -0.0665 0.5948 0.0187
-5.500 -0.1953 0.03819 0.03368 -0.0676 0.5848 0.0193
-5.250 -0.1685 0.03515 0.03040 -0.0691 0.5765 0.0203
-5.000 -0.1397 0.03020 0.02501 -0.0708 0.5704 0.0216
-4.750 -0.1100 0.02418 0.01829 -0.0721 0.5649 0.0235
-4.500 -0.0828 0.02228 0.01612 -0.0728 0.5587 0.0240
-4.250 -0.0548 0.02113 0.01479 -0.0733 0.5530 0.0244
-4.000 -0.0268 0.02041 0.01392 -0.0737 0.5472 0.0250
-3.750 0.0015 0.01964 0.01300 -0.0741 0.5421 0.0257
-3.500 0.0304 0.01837 0.01150 -0.0745 0.5375 0.0262
-3.250 0.0594 0.01729 0.01020 -0.0748 0.5331 0.0266
-3.000 0.0883 0.01638 0.00907 -0.0751 0.5293 0.0270
-2.750 0.1173 0.01558 0.00811 -0.0754 0.5258 0.0274
-2.500 0.1463 0.01488 0.00727 -0.0756 0.5223 0.0277
-2.250 0.1752 0.01434 0.00661 -0.0759 0.5187 0.0281
-2.000 0.2040 0.01390 0.00606 -0.0761 0.5151 0.0287
-1.750 0.2329 0.01341 0.00547 -0.0763 0.5119 0.0289
-1.500 0.2618 0.01295 0.00495 -0.0765 0.5089 0.0291
-1.250 0.2907 0.01257 0.00452 -0.0767 0.5053 0.0294
-1.000 0.3195 0.01227 0.00417 -0.0770 0.5013 0.0298
-0.750 0.3482 0.01205 0.00388 -0.0772 0.4976 0.0302
-0.500 0.3771 0.01184 0.00366 -0.0774 0.4943 0.0305
-0.250 0.4061 0.01167 0.00348 -0.0777 0.4912 0.0308
0.000 0.4351 0.01136 0.00314 -0.0780 0.4880 0.0314
0.250 0.4640 0.01117 0.00292 -0.0783 0.4847 0.0321
0.500 0.4929 0.01105 0.00277 -0.0786 0.4816 0.0331
0.750 0.5220 0.01094 0.00268 -0.0789 0.4784 0.0345
1.000 0.5510 0.01087 0.00261 -0.0791 0.4751 0.0354
1.250 0.5799 0.01083 0.00257 -0.0794 0.4721 0.0362
1.500 0.6087 0.01082 0.00253 -0.0797 0.4684 0.0374
1.750 0.6376 0.01080 0.00251 -0.0799 0.4633 0.0393
2.250 0.6952 0.01071 0.00255 -0.0805 0.4532 0.1060
2.750 0.7464 0.00878 0.00271 -0.0801 0.4445 1.0000
3.000 0.7750 0.00888 0.00277 -0.0803 0.4397 1.0000
3.250 0.8036 0.00898 0.00284 -0.0806 0.4339 1.0000
3.500 0.8321 0.00908 0.00291 -0.0808 0.4238 1.0000
3.750 0.8606 0.00919 0.00299 -0.0810 0.4146 1.0000
4.000 0.8888 0.00932 0.00308 -0.0812 0.4044 1.0000
4.250 0.9169 0.00947 0.00320 -0.0814 0.3920 1.0000
4.500 0.9448 0.00965 0.00332 -0.0816 0.3748 1.0000
4.750 0.9721 0.00993 0.00349 -0.0817 0.3488 1.0000
5.000 0.9965 0.01070 0.00390 -0.0817 0.2781 1.0000
5.250 1.0215 0.01138 0.00437 -0.0816 0.2377 1.0000
5.500 1.0467 0.01197 0.00481 -0.0816 0.2102 1.0000
5.750 1.0718 0.01254 0.00524 -0.0815 0.1803 1.0000
6.250 1.1152 0.01457 0.00666 -0.0806 0.0645 1.0000
6.500 1.1407 0.01494 0.00704 -0.0805 0.0589 1.0000
6.750 1.1662 0.01527 0.00742 -0.0804 0.0555 1.0000
7.000 1.1910 0.01569 0.00784 -0.0802 0.0509 1.0000
7.250 1.2155 0.01612 0.00828 -0.0799 0.0462 1.0000
7.500 1.2400 0.01651 0.00867 -0.0797 0.0388 1.0000
7.750 1.2600 0.01739 0.00940 -0.0789 0.0167 1.0000
8.000 1.2816 0.01805 0.01010 -0.0782 0.0139 1.0000
8.250 1.3034 0.01864 0.01076 -0.0775 0.0126 1.0000
8.500 1.3248 0.01922 0.01141 -0.0768 0.0117 1.0000
8.750 1.3449 0.01988 0.01216 -0.0760 0.0108 1.0000
9.000 1.3634 0.02063 0.01298 -0.0749 0.0099 1.0000
9.250 1.3788 0.02158 0.01402 -0.0734 0.0092 1.0000
9.500 1.3943 0.02243 0.01495 -0.0719 0.0088 1.0000
9.750 1.4085 0.02327 0.01588 -0.0702 0.0085 1.0000
10.000 1.4196 0.02422 0.01691 -0.0681 0.0082 1.0000
10.250 1.4254 0.02531 0.01811 -0.0653 0.0079 1.0000
10.500 1.4309 0.02661 0.01949 -0.0629 0.0076 1.0000
10.750 1.4363 0.02809 0.02106 -0.0609 0.0073 1.0000
11.000 1.4414 0.02978 0.02284 -0.0594 0.0071 1.0000
11.250 1.4453 0.03176 0.02491 -0.0582 0.0068 1.0000
11.500 1.4468 0.03422 0.02745 -0.0574 0.0066 1.0000
11.750 1.4431 0.03742 0.03077 -0.0568 0.0063 1.0000
12.000 1.4448 0.04017 0.03362 -0.0565 0.0062 1.0000
12.250 1.4464 0.04299 0.03655 -0.0564 0.0061 1.0000
12.500 1.4465 0.04603 0.03970 -0.0563 0.0060 1.0000
12.750 1.4459 0.04917 0.04297 -0.0563 0.0059 1.0000
13.000 1.4442 0.05244 0.04634 -0.0562 0.0058 1.0000
13.250 1.4419 0.05578 0.04978 -0.0562 0.0057 1.0000
13.500 1.4392 0.05917 0.05328 -0.0562 0.0056 1.0000
13.750 1.4358 0.06262 0.05683 -0.0562 0.0055 1.0000
14.000 1.4326 0.06609 0.06040 -0.0563 0.0053 1.0000
14.250 1.4295 0.06966 0.06407 -0.0564 0.0053 1.0000
14.500 1.4266 0.07324 0.06775 -0.0567 0.0052 1.0000
14.750 1.4238 0.07687 0.07147 -0.0571 0.0051 1.0000
15.000 1.4210 0.08056 0.07526 -0.0575 0.0050 1.0000
15.250 1.4182 0.08434 0.07913 -0.0580 0.0049 1.0000
15.500 1.4153 0.08816 0.08304 -0.0586 0.0048 1.0000
15.750 1.4123 0.09202 0.08700 -0.0593 0.0048 1.0000
16.000 1.4089 0.09603 0.09112 -0.0601 0.0047 1.0000
16.250 1.4055 0.10010 0.09528 -0.0611 0.0046 1.0000
16.500 1.4019 0.10422 0.09950 -0.0621 0.0046 1.0000
16.750 1.3975 0.10852 0.10389 -0.0632 0.0045 1.0000
17.000 1.3926 0.11291 0.10837 -0.0644 0.0044 1.0000
17.250 1.3867 0.11748 0.11304 -0.0657 0.0044 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il)