GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.62 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe167-il-1000000-n5.txt Download as CSV file: xf-goe167-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4203 0.08494 0.08223 -0.0196 0.6319 0.0088
-8.250 -0.4175 0.08089 0.07814 -0.0233 0.6183 0.0092
-8.000 -0.4208 0.06921 0.06643 -0.0372 0.6131 0.0106
-7.750 -0.4035 0.06586 0.06299 -0.0415 0.5998 0.0108
-7.500 -0.3846 0.06269 0.05973 -0.0453 0.5877 0.0110
-7.250 -0.3647 0.05923 0.05618 -0.0493 0.5771 0.0114
-6.750 -0.3243 0.04167 0.03811 -0.0639 0.5650 0.0141
-6.250 -0.2786 0.02333 0.01861 -0.0704 0.5548 0.0181
-6.000 -0.2511 0.02297 0.01816 -0.0707 0.5477 0.0183
-5.750 -0.2236 0.02236 0.01742 -0.0711 0.5418 0.0185
-5.500 -0.1960 0.02157 0.01651 -0.0715 0.5366 0.0188
-5.250 -0.1682 0.02089 0.01570 -0.0719 0.5311 0.0191
-5.000 -0.1403 0.02001 0.01467 -0.0723 0.5264 0.0196
-4.750 -0.1120 0.01824 0.01264 -0.0728 0.5222 0.0202
-4.500 -0.0835 0.01673 0.01087 -0.0732 0.5181 0.0210
-4.250 -0.0549 0.01587 0.00983 -0.0735 0.5143 0.0217
-4.000 -0.0261 0.01511 0.00890 -0.0738 0.5111 0.0222
-3.750 0.0027 0.01448 0.00815 -0.0741 0.5080 0.0224
-3.500 0.0316 0.01392 0.00746 -0.0744 0.5047 0.0226
-3.250 0.0605 0.01347 0.00691 -0.0747 0.5013 0.0228
-3.000 0.0894 0.01303 0.00637 -0.0750 0.4979 0.0229
-2.750 0.1184 0.01263 0.00590 -0.0752 0.4953 0.0230
-2.500 0.1474 0.01223 0.00543 -0.0755 0.4923 0.0231
-2.250 0.1763 0.01173 0.00486 -0.0758 0.4887 0.0232
-2.000 0.2051 0.01091 0.00394 -0.0761 0.4850 0.0239
-1.750 0.2340 0.01056 0.00354 -0.0764 0.4816 0.0242
-1.500 0.2631 0.01026 0.00322 -0.0767 0.4788 0.0246
-1.250 0.2922 0.01005 0.00300 -0.0770 0.4757 0.0250
-1.000 0.3213 0.00990 0.00282 -0.0773 0.4723 0.0255
-0.750 0.3503 0.00977 0.00267 -0.0775 0.4687 0.0260
-0.500 0.3795 0.00966 0.00254 -0.0778 0.4659 0.0265
-0.250 0.4086 0.00954 0.00242 -0.0781 0.4637 0.0270
0.000 0.4378 0.00944 0.00231 -0.0784 0.4612 0.0275
0.250 0.4669 0.00936 0.00221 -0.0787 0.4580 0.0279
0.500 0.4960 0.00930 0.00213 -0.0790 0.4548 0.0283
0.750 0.5251 0.00925 0.00206 -0.0793 0.4504 0.0286
1.000 0.5542 0.00920 0.00200 -0.0796 0.4443 0.0290
1.250 0.5832 0.00919 0.00197 -0.0799 0.4397 0.0296
1.500 0.6122 0.00918 0.00195 -0.0802 0.4357 0.0301
1.750 0.6412 0.00916 0.00193 -0.0805 0.4306 0.0305
2.000 0.6701 0.00917 0.00194 -0.0808 0.4247 0.0309
2.250 0.6990 0.00918 0.00192 -0.0810 0.4200 0.0338
2.500 0.7279 0.00919 0.00195 -0.0813 0.4127 0.0397
2.750 0.7567 0.00915 0.00202 -0.0817 0.4040 0.1102
3.250 0.8082 0.00749 0.00227 -0.0816 0.3760 1.0000
3.500 0.8364 0.00770 0.00238 -0.0818 0.3544 1.0000
3.750 0.8622 0.00843 0.00272 -0.0819 0.2799 1.0000
4.000 0.8885 0.00903 0.00307 -0.0821 0.2328 1.0000
4.250 0.9161 0.00933 0.00329 -0.0822 0.2164 1.0000
4.500 0.9437 0.00960 0.00349 -0.0824 0.2044 1.0000
4.750 0.9712 0.00986 0.00369 -0.0826 0.1915 1.0000
5.000 0.9950 0.01082 0.00423 -0.0825 0.1132 1.0000
5.250 1.0194 0.01161 0.00480 -0.0823 0.0624 1.0000
5.500 1.0465 0.01186 0.00503 -0.0824 0.0571 1.0000
5.750 1.0735 0.01211 0.00528 -0.0825 0.0542 1.0000
6.000 1.1001 0.01240 0.00555 -0.0825 0.0502 1.0000
6.250 1.1267 0.01268 0.00583 -0.0826 0.0464 1.0000
6.500 1.1535 0.01291 0.00607 -0.0826 0.0450 1.0000
6.750 1.1795 0.01323 0.00636 -0.0826 0.0391 1.0000
7.000 1.2030 0.01388 0.00686 -0.0822 0.0165 1.0000
7.250 1.2281 0.01429 0.00727 -0.0820 0.0128 1.0000
7.500 1.2533 0.01464 0.00765 -0.0819 0.0117 1.0000
7.750 1.2779 0.01505 0.00809 -0.0816 0.0105 1.0000
8.000 1.3017 0.01553 0.00861 -0.0813 0.0091 1.0000
8.250 1.3259 0.01593 0.00903 -0.0810 0.0086 1.0000
8.500 1.3495 0.01636 0.00950 -0.0806 0.0081 1.0000
8.750 1.3725 0.01682 0.01001 -0.0801 0.0075 1.0000
9.000 1.3946 0.01735 0.01056 -0.0795 0.0070 1.0000
9.250 1.4153 0.01798 0.01123 -0.0787 0.0065 1.0000
9.500 1.4357 0.01858 0.01187 -0.0779 0.0062 1.0000
9.750 1.4562 0.01913 0.01246 -0.0771 0.0059 1.0000
10.000 1.4755 0.01972 0.01311 -0.0761 0.0056 1.0000
10.250 1.4934 0.02038 0.01382 -0.0750 0.0053 1.0000
10.500 1.5097 0.02107 0.01456 -0.0736 0.0051 1.0000
10.750 1.5240 0.02182 0.01536 -0.0719 0.0049 1.0000
11.000 1.5344 0.02267 0.01626 -0.0696 0.0047 1.0000
11.250 1.5396 0.02375 0.01740 -0.0667 0.0045 1.0000
11.500 1.5421 0.02520 0.01895 -0.0639 0.0043 1.0000
11.750 1.5481 0.02661 0.02045 -0.0620 0.0043 1.0000
12.000 1.5546 0.02816 0.02209 -0.0606 0.0042 1.0000
12.250 1.5601 0.02996 0.02397 -0.0594 0.0041 1.0000
12.500 1.5649 0.03201 0.02611 -0.0586 0.0040 1.0000
12.750 1.5689 0.03428 0.02848 -0.0581 0.0040 1.0000
13.000 1.5718 0.03680 0.03109 -0.0577 0.0039 1.0000
13.250 1.5741 0.03948 0.03387 -0.0575 0.0038 1.0000
13.500 1.5754 0.04231 0.03679 -0.0574 0.0037 1.0000
13.750 1.5761 0.04524 0.03981 -0.0574 0.0036 1.0000
14.000 1.5760 0.04832 0.04299 -0.0574 0.0035 1.0000
14.250 1.5752 0.05145 0.04621 -0.0574 0.0035 1.0000
14.500 1.5738 0.05466 0.04950 -0.0575 0.0034 1.0000
14.750 1.5713 0.05802 0.05294 -0.0576 0.0033 1.0000
15.000 1.5682 0.06146 0.05646 -0.0578 0.0033 1.0000
15.250 1.5641 0.06508 0.06017 -0.0580 0.0032 1.0000
15.500 1.5601 0.06877 0.06395 -0.0584 0.0031 1.0000
15.750 1.5557 0.07261 0.06786 -0.0588 0.0031 1.0000
16.000 1.5496 0.07669 0.07204 -0.0594 0.0031 1.0000
16.250 1.5429 0.08097 0.07640 -0.0600 0.0030 1.0000
16.500 1.5356 0.08541 0.08094 -0.0608 0.0030 1.0000
16.750 1.5270 0.09010 0.08573 -0.0618 0.0029 1.0000
17.000 1.5175 0.09496 0.09069 -0.0628 0.0029 1.0000
17.250 1.5064 0.10018 0.09602 -0.0641 0.0028 1.0000
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Polar data table (+)
Polar graphs
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