BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-8 AIRFOIL (vr8-il) Reynolds number: 200,000 Max Cl/Cd: 44.34 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr8-il-200000-n5.txt Download as CSV file: xf-vr8-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-8 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5595 0.08217 0.07875 -0.0124 1.0000 0.0119
-8.500 -0.5609 0.07818 0.07480 -0.0149 1.0000 0.0117
-8.250 -0.5672 0.07311 0.06977 -0.0196 1.0000 0.0116
-8.000 -0.5722 0.06838 0.06500 -0.0225 1.0000 0.0114
-7.750 -0.5733 0.06374 0.06030 -0.0248 1.0000 0.0112
-7.500 -0.5734 0.05856 0.05499 -0.0266 1.0000 0.0112
-7.250 -0.5701 0.05370 0.04996 -0.0275 1.0000 0.0111
-7.000 -0.5640 0.04896 0.04499 -0.0278 1.0000 0.0110
-6.750 -0.5557 0.04414 0.03989 -0.0274 1.0000 0.0110
-6.250 -0.5308 0.03659 0.03171 -0.0256 1.0000 0.0131
-6.000 -0.5153 0.03345 0.02823 -0.0244 1.0000 0.0143
-5.750 -0.4995 0.02977 0.02410 -0.0228 1.0000 0.0144
-5.500 -0.4819 0.02631 0.02010 -0.0209 1.0000 0.0148
-5.250 -0.4621 0.02351 0.01653 -0.0189 1.0000 0.0156
-5.000 -0.4416 0.02143 0.01429 -0.0179 1.0000 0.0165
-4.750 -0.4199 0.02014 0.01280 -0.0169 1.0000 0.0188
-4.500 -0.3983 0.01841 0.01081 -0.0157 1.0000 0.0208
-4.250 -0.3762 0.01709 0.00937 -0.0146 1.0000 0.0218
-4.000 -0.3444 0.01587 0.00802 -0.0155 0.9938 0.0233
-3.750 -0.3100 0.01479 0.00695 -0.0172 0.9846 0.0255
-3.500 -0.2765 0.01390 0.00602 -0.0186 0.9723 0.0262
-3.250 -0.2429 0.01320 0.00527 -0.0199 0.9569 0.0270
-2.750 -0.1618 0.01240 0.00384 -0.0243 0.7828 0.0303
-2.500 -0.1389 0.01235 0.00339 -0.0230 0.7154 0.0309
-2.250 -0.1147 0.01228 0.00301 -0.0221 0.6663 0.0318
-2.000 -0.0901 0.01226 0.00265 -0.0213 0.6183 0.0333
-1.750 -0.0645 0.01223 0.00237 -0.0209 0.5840 0.0352
-1.500 -0.0381 0.01212 0.00214 -0.0206 0.5635 0.0388
-1.250 -0.0116 0.01205 0.00194 -0.0203 0.5446 0.0422
-1.000 0.0144 0.01195 0.00176 -0.0200 0.5178 0.0582
-0.750 0.0333 0.01037 0.00155 -0.0194 0.4840 0.4790
-0.500 0.0588 0.01022 0.00150 -0.0190 0.4628 0.5412
-0.250 0.0844 0.01011 0.00147 -0.0186 0.4409 0.5954
0.000 0.1068 0.00977 0.00149 -0.0173 0.4235 0.7024
0.250 0.1310 0.00964 0.00151 -0.0163 0.4105 0.7601
0.500 0.1474 0.01131 0.00186 -0.0150 0.0450 0.7921
0.750 0.1733 0.01133 0.00192 -0.0144 0.0420 0.8275
1.000 0.2011 0.01139 0.00201 -0.0141 0.0396 0.8669
1.250 0.2350 0.01146 0.00211 -0.0152 0.0392 0.9076
1.500 0.2708 0.01156 0.00220 -0.0169 0.0388 0.9386
1.750 0.2989 0.01170 0.00234 -0.0170 0.0385 0.9692
2.000 0.3548 0.01177 0.00242 -0.0232 0.0378 0.9996
2.250 0.3796 0.01190 0.00255 -0.0227 0.0377 1.0000
2.500 0.4037 0.01205 0.00270 -0.0221 0.0374 1.0000
2.750 0.4278 0.01223 0.00287 -0.0214 0.0352 1.0000
3.000 0.4520 0.01238 0.00308 -0.0208 0.0341 1.0000
3.250 0.4762 0.01256 0.00329 -0.0201 0.0331 1.0000
3.500 0.5005 0.01275 0.00353 -0.0195 0.0320 1.0000
3.750 0.5247 0.01296 0.00380 -0.0189 0.0310 1.0000
4.000 0.5489 0.01321 0.00415 -0.0182 0.0295 1.0000
4.250 0.5728 0.01351 0.00451 -0.0176 0.0291 1.0000
4.500 0.5967 0.01384 0.00490 -0.0169 0.0289 1.0000
4.750 0.6205 0.01421 0.00534 -0.0162 0.0287 1.0000
5.000 0.6440 0.01461 0.00583 -0.0156 0.0287 1.0000
5.250 0.6674 0.01507 0.00642 -0.0149 0.0286 1.0000
5.500 0.6904 0.01558 0.00701 -0.0141 0.0283 1.0000
5.750 0.7134 0.01609 0.00760 -0.0135 0.0273 1.0000
6.000 0.7357 0.01670 0.00828 -0.0127 0.0268 1.0000
6.250 0.7574 0.01742 0.00908 -0.0118 0.0264 1.0000
6.500 0.7783 0.01825 0.00996 -0.0109 0.0258 1.0000
6.750 0.7980 0.01929 0.01105 -0.0099 0.0245 1.0000
7.000 0.8159 0.02081 0.01245 -0.0089 0.0230 1.0000
7.250 0.8355 0.02270 0.01434 -0.0079 0.0210 1.0000
7.500 0.8570 0.02489 0.01664 -0.0071 0.0193 1.0000
7.750 0.8802 0.02767 0.01943 -0.0067 0.0174 1.0000
8.000 0.8979 0.02910 0.02139 -0.0055 0.0151 1.0000
8.250 0.9136 0.03074 0.02360 -0.0039 0.0129 1.0000
8.500 0.9307 0.03280 0.02593 -0.0029 0.0119 1.0000
8.750 0.9447 0.03521 0.02869 -0.0016 0.0113 1.0000
9.000 0.9512 0.03853 0.03270 0.0006 0.0106 1.0000
9.250 0.9549 0.04206 0.03672 0.0025 0.0102 1.0000
9.500 0.9541 0.04573 0.04080 0.0045 0.0099 1.0000
9.750 0.9503 0.04907 0.04446 0.0062 0.0095 1.0000
10.000 0.9407 0.05221 0.04786 0.0082 0.0094 1.0000
10.250 0.9246 0.05577 0.05165 0.0095 0.0093 1.0000
10.500 0.9090 0.05964 0.05570 0.0091 0.0092 1.0000
10.750 0.8958 0.06380 0.06001 0.0071 0.0091 1.0000
11.000 0.8664 0.07201 0.06843 0.0019 0.0095 1.0000
11.250 0.8421 0.08091 0.07747 -0.0047 0.0101 1.0000
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Polar data table (+)
Polar graphs
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